@A300-600

SERVICE BULLETIN

SUMMARY

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX

FRANCE

Tel : (33) 5 61 93 33 33

Telex : AIRBU 530526F

Fax : (33) 5 61 93 42 51

This summary is for information only and is not approved for modification of the aircraft.

MANDATORY MANDATORY MANDATORY

ATA SYSTEM: 53

TITLE: FUSELAGE - CENTER FUSELAGE - INSPECT LOWER FRAME BASE

FITTING BETWEEN FRAMES 41 AND 46

**CONF ALL

MODIFICATIONS

None

REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

During a routine maintenance on A300-600 aircraft, operators have reported separate instances of

cracks in the Frame feet fittings, connecting the Frame lower positions to the centre wing box (air

conditioning bay).

Since this time, AIRBUS has carried out a sampling inspection program on both aircraft types (A300

and A300-600).

During this sampling program, twenty three A300-600 aircraft were inspected and cracks were found on

the lower Frame fittings of Frame 44 to Frame 46 (LH and RH) on twenty two of the inspected aircraft.

The aircraft with the findings have accumulated between 8000 and 21000 Flight Cycles (FC) and the

lengths of the cracks varied between 12 mm and 18 mm (0.472 in. and 0.709 in.).

Service Bulletin No. A300-53-6111 was created in order to treat the affected areas by repetitive

inspection and also repair in case of crack finding. Repaired Frames were no longer inspected up to

aircraft Limit of Validity (LoV).

Further to new findings on repaired Frame feet, a new detailed Finite Element Model (FEM) study was

performed. Outcomes of this study led Airbus to review the inspection program.

The aim of the Service Bulletin, depending of the accomplishment of Service Bulletin No.

A300-53-6111, is to perform a Detailed Inspection (DET) of the lower Frame feet fittings between

Frame 41 and Frame 46 for the entire fleet.

In case of crack finding, two options are possible:

- The cracked Frame foot is replaced by an identical new one and the Inspection Service Bulletin

(ISB) No. A300-53-6177 is still applicable.

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 1

5

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@A300-600

SERVICE BULLETIN

SUMMARY

- All Frame feet are replaced by new optimized parts as per Modification Service Bulletin No.

A300-53-6176 (Mod. No. 13721S22901). In this case, no further inspection is necessary.

Any findings (including Nil findings) are to be reported to AIRBUS.

Service Bulletin No. A300-53-6111 is therefore cancelled and superseded by this new ISB. In addition

to this new inspection program, Airbus designed new Frame feet. Their installation is proposed through

a dedicated modification Service Bulletin No. A300-53-6176. Accomplishment of Modification Service

Bulletin No. A300-53-6176 cancels the requirements of this ISB.

Accomplishment of this ISB will allow early detection of cracks in order to avoid possible occurrence of

crack propagation which can lead to costly and time-consuming repairs.

GENERAL EVALUATION

EVALUATION TABLE

COMPLIANCE MANDATORY (1) CANCELS INSPECTION SB NO

POTENTIAL AD YES A/C OPERATION AFFECTED NO

RELIABILITY AFFECTED NO PAX COMFORT AFFECTED NO

COST SAVING NO ETOPS AFFECTED NO

STRUCTURAL LIFE EXTN NO VENDOR SB INVOLVED NO

DE-FUELLING/VENTILATION YES

NOTE (1): Service Bulletin must be accomplished.

MATERIAL PRICE INFORMATION

**CONF 001

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Kit 536177A03R00 1 8,100.00 Frame foot, Screws, Nuts, Rivets

Kit 536177A06R00 1 8,900.00 Frame foot, Screws, Nuts, Rivets

Kit 536177A09R00 1 7,600.00 Frame foot, Screws, Nuts, Rivets

Kit 536177A12R00 1 7,300.00 Frame foot, Screws, Nuts, Rivets

Kit 536177A15R00 1 7,900.00 Frame foot, Screws, Nuts, Rivets

Kit 536177A18R00 1 8,700.00 Frame foot, Screws, Nuts, Rivets

Kit 536177A21R00 1 8,100.00 Frame foot, Screws, Nuts, Rivets

Kit 536177A24R00 1 9,000.00 Frame foot, Screws, Nuts, Rivets

Kit 536177A27R00 1 7,600.00 Frame foot, Screws, Nuts, Rivets

Kit 536177A30R00 1 7,300.00 Frame foot, Screws, Nuts, Rivets

Kit 536177A33R00 1 7,900.00 Frame foot, Screws, Nuts, Rivets

Kit 536177A36R00 1 8,700.00 Frame foot, Screws, Nuts, Rivets

TOTAL 97,100.00

Component COMPA01 2 See SB Screws, Nuts, Rivets

Component COMPA02 4 See SB Screws, Nuts, Rivets

Component COMPA03 2 See SB Screws, Nuts, Rivets

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 2

5

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

SERVICE BULLETIN

SUMMARY

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Component COMPA04 2 See SB Screws, Nuts, Rivets

Component COMPA05 2 See SB Screws, Nuts, Rivets

**CONF 002

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Kit 536177A02R00 1 7,600.00 Frame foot, Screws, Nuts, Rivets

Kit 536177A05R00 1 8,200.00 Frame foot, Screws, Nuts, Rivets

Kit 536177A08R00 1 7,100.00 Frame foot, Screws, Nuts, Rivets

Kit 536177A11R00 1 6,700.00 Frame foot, Screws, Nuts, Rivets

Kit 536177A14R00 1 7,300.00 Frame foot, Screws, Nuts, Rivets

Kit 536177A17R00 1 8,200.00 Frame foot, Screws, Nuts, Rivets

Kit 536177A20R00 1 7,600.00 Frame foot, Screws, Nuts, Rivets

Kit 536177A23R00 1 8,200.00 Frame foot, Screws, Nuts, Rivets

Kit 536177A26R00 1 7,100.00 Frame foot, Screws, Nuts, Rivets

Kit 536177A29R00 1 6,700.00 Frame foot, Screws, Nuts, Rivets

Kit 536177A32R00 1 7,300.00 Frame foot, Screws, Nuts, Rivets

Kit 536177A35R00 1 8,200.00 Frame foot, Screws, Nuts, Rivets

TOTAL 90,200.00

Component COMPA01 2 See SB Screws, Nuts, Rivets

Component COMPA02 4 See SB Screws, Nuts, Rivets

Component COMPA03 2 See SB Screws, Nuts, Rivets

Component COMPA04 2 See SB Screws, Nuts, Rivets

Component COMPA05 2 See SB Screws, Nuts, Rivets

**CONF 003

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Kit 536177A01R00 1 7,400.00 Frame foot, Screws, Nuts, Rivets

Kit 536177A04R00 1 8,100.00 Frame foot, Screws, Nuts, Rivets

Kit 536177A07R00 1 7,000.00 Frame foot, Screws, Nuts, Rivets

Kit 536177A10R00 1 6,600.00 Frame foot, Screws, Nuts, Rivets

Kit 536177A13R00 1 7,200.00 Frame foot, Screws, Nuts, Rivets

Kit 536177A16R00 1 8,200.00 Frame foot, Screws, Nuts, Rivets

Kit 536177A19R00 1 7,400.00 Frame foot, Screws, Nuts, Rivets

Kit 536177A22R00 1 8,100.00 Frame foot, Screws, Nuts, Rivets

Kit 536177A25R00 1 7,000.00 Frame foot, Screws, Nuts, Rivets

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 3

5

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

SERVICE BULLETIN

SUMMARY

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Kit 536177A28R00 1 6,600.00 Frame foot, Screws, Nuts, Rivets

Kit 536177A31R00 1 7,200.00 Frame foot, Screws, Nuts, Rivets

Kit 536177A34R00 1 8,100.00 Frame foot, Screws, Nuts, Rivets

TOTAL 88,900.00

Component COMPA01 2 See SB Screws, Nuts, Rivets

Component COMPA02 4 See SB Screws, Nuts, Rivets

Component COMPA03 2 See SB Screws, Nuts, Rivets

Component COMPA04 2 See SB Screws, Nuts, Rivets

Component COMPA05 2 See SB Screws, Nuts, Rivets

**CONF 004

No Material

EFFECTIVITY

**CONF ALL

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

06P 67Q ABR AHK BCS F2I FDX IRA IRM KAC MNB MRJ MSR

OHY SUD TAR THA UPS UQA URS UTP UZB

CONCURRENT REQUIREMENTS

None

REFERENCES / REPERCUSSIONS

TFU None

OEB None

AOT None

SIL None

LINE MAINTENANCE AFFECTED No

LIFE LIMIT None

OTHER None

NATURE OF THE WORK

AIRCRAFT YES

EQUIPMENT NO

HARD NO

SOFT NO

OBRM NO

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 4

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

SERVICE BULLETIN

SUMMARY

MANPOWER

**CONF 001

Task 536177-832-801-001: Detailed Inspection of the Frame foot

TOTAL MANHOURS 8.00

ELAPSED TIME (HOURS) 2.50

Task 536177-833-801-001: Repair

TOTAL MANHOURS 541.00

ELAPSED TIME (HOURS) 42.00

**CONF 002

Task 536177-832-801-001: Detailed Inspection of the Frame foot

TOTAL MANHOURS 8.00

ELAPSED TIME (HOURS) 2.50

Task 536177-833-801-001: Repair

TOTAL MANHOURS 541.00

ELAPSED TIME (HOURS) 42.00

**CONF 003

Task 536177-832-801-001: Detailed Inspection of the Frame foot

TOTAL MANHOURS 8.00

ELAPSED TIME (HOURS) 2.50

Task 536177-833-801-001: Repair

TOTAL MANHOURS 541.00

ELAPSED TIME (HOURS) 42.00

**CONF 004

Task 536177-839-801-001: Contact and Report to AIRBUS

TOTAL MANHOURS 0.50

ELAPSED TIME (HOURS) 0.50

APPENDICES

**CONF ALL

Appendix 01 - Elapsed Time Assumptions

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 5

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@A300-600

SERVICE BULLETIN

SUMMARY

**CONF ALL

FR41

FR42

FR43

FR44

FR45

FR46

FR47

FR40

FR46

FR45

FR44

FR43

FR42

FR41

AREAS TO BE INSPECTED

CL

A

B

Z140

A

B

D_SB_536177_5_SAAA_01_01

Figure A-FSAAA - Sheet 01

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 6

5

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 - CENTER FUSELAGE - INSPECT LOWER FRAME BASE

FITTING BETWEEN FRAMES 41 AND 46

MODIFICATION No.: None

This document contains AIRBUS PROPRIETARY INFORMATION and shall at all times remain the

property of AIRBUS; no intellectual property right or licence is granted by AIRBUS in connection with

any information contained in it. It is delivered on the express condition that said document and the

information contained in it shall be treated as confidential, shall not be used for any purpose other than

that for which it is hereby delivered. It shall not be disclosed in whole or in part to third parties and shall

not be duplicated in any manner (except for the purposes of performing the tasks described hereunder

and provided that any recipient of such document shall comply with the conditions herein), without

AIRBUS prior written consent.

1. PLANNING INFORMATION

**CONF ALL

A. EFFECTIVITY

(1) Models

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

F4-622R

(2) Effectivity by MSN

0294 0344 0358 0361 0365 0380 0388 0401 0405 0408 0411 0414 0417 0477 0479

0505 0521 0525 0529-0530 0532 0536 0543 0546 0553 0555 0557-0559 0561 0563

0572 0575 0579 0581 0584 0602-0603 0607-0608 0611 0613 0617-0618 0621 0623

0625-0626 0629-0630 0632-0633 0637 0641 0643 0657 0659 0664 0666 0668 0670

0673 0677 0679 0683 0688 0694 0696 0699 0701 0703 0707 0709 0711 0713 0715

0717 0719 0721-0730 0732-0750 0752-0764 0766 0768-0775 0777-0794 0797

0799-0840 0845-0878

(3) Effectivity by Operator

The Operator/MSN relationship is provided for information only and is correct at the time

of issue in accordance with the information available to AIRBUS. Any future changes

resulting from transfer of an aircraft from one operator to another will not be reflected in

this list unless the Service Bulletin is revised for another reason.

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 1

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

SERVICE BULLETIN

OPERATOR MSN

06P 0788

67Q 0584 0603 0744 0749 0764

ABR 0677 0743

AHK 0683 0770 0855 0856 0857 0858 0859 0860 0870 0871

BCS 0529 0557 0602 0617 0621 0637 0641 0670 0679 0703 0711 0724

0729 0730 0737 0740 0753 0783 0797 0836 0837 0872

F2I 0294

FDX 0358 0361 0365 0388 0417 0477 0479 0530 0536 0543 0555 0559

0572 0575 0579 0581 0611 0613 0625 0630 0633 0657 0659 0664

0668 0688 0709 0713 0715 0726 0728 0735 0736 0738 0742 0745

0748 0752 0757 0759 0760 0761 0766 0768 0769 0771 0772 0774

0777 0778 0779 0780 0781 0789 0790 0791 0792 0793 0794 0799

0800 0801 0802 0803 0804 0873 0874 0875 0876 0877 0878

IRA 0632 0696 0723 0727

IRM 0380 0401 0405 0408 0411 0414 0546 0553 0608 0618 0623 0701

0773 0838

KAC 0344 0673 0694 0699 0719 0721

MNB 0521 0525 0532 0734 0739 0755 0756 0758

MRJ 0750 0762

MSR 0561 0607

OHY 0747

SUD 0666 0775

TAR 0505 0558 0563

THA 0629 0782 0784 0785 0786 0787

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

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

0829 0830 0831 0832 0833 0834 0835 0839 0840 0845 0846 0847

0848 0849 0850 0851 0852 0853 0854 0861 0862 0863 0864 0865

0866 0867 0868 0869

UQA 0626 0643

URS 0733

UTP 0707 0725 0732 0741 0746 0754 0763

UZB 0717 0722

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 2

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

SERVICE BULLETIN

(4) Configuration by MSN

MSN CONFIGURATION

0294 0344 0358 0361 0365 0380 0388 0401 0405 0408 0411

0414 0417 0477 0479 0505 0521 0525 0529 0530 0532 0536

0543 0546 0553 0555 0557 0558 0559 0561 0563 0572 0575

0579 0581 0584 0602 0603 0607 0608 0611 0613 0617 0618

0621 0623 0625 0626 0629 0630 0632 0633 0637 0641 0643

0657 0659 0664 0666 0668 0670 0673 0677 0679 0683 0688

0694 0696 0699 0701 0703 0707 0709 0711 0713 0715 0717

0719 0721 0722 0723 0724 0725 0726 0727 0728 0729 0730

0732 0733 0734 0735 0736 0737 0738 0739 0740 0741 0742

0743 0744 0745 0746 0747 0748 0749 0750 0752 0753 0754

0755 0756 0757 0758 0759 0760 0761 0762 0763 0764 0766

0768 0769 0770 0771 0772 0773 0774 0775 0777 0778 0779

0780 0781 0782 0783 0784 0785 0786 0787 0788 0789 0790

0791 0792 0793 0794 0797 0799 0800 0801 0802 0803 0804

0805 0806 0807 0808 0809 0810 0811 0812 0813 0814 0815

0816 0817 0818 0819 0820 0821 0822 0823 0824 0825 0826

0827 0828 0829 0830 0831 0832 0833 0834 0835 0836 0837

0838 0839 0840 0845 0846 0847 0848 0849 0850 0851 0852

0853 0854 0855 0856 0857 0858 0859 0860 0861 0862 0863

0864 0865 0866 0867 0868 0869 0870 0871 0872 0873 0874

0875 0876 0877 0878

001 002 003 004

(5) Configuration definition

NOTE: Each Frame Foot is independent, operator must define which repair has

been applied or not on each frame foot and choose the configuration

defined below that applies for each frame foot.

**CONF 001

Config. 001 is valid for Frame foot never repaired (either already inspected as per

Service Bulletin No. A300-53-6111 or not).

**CONF 002

Config. 002 is valid for Frame foot preventively repaired (no crack) as per Service

Bulletin No. A300-53-6111.

**CONF 003

Config. 003 is valid for Frame foot repaired in Area 1 as per Service Bulletin No.

A300-53-6111 or as per R53810322 or R53810323 or R53810329 or R53810330 or

R53810331 or R53810332.

**CONF 004

Config. 004 is valid for Frame foot in any other situation (not covered by Config. 001,

Config. 002 or Config. 003).

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 3

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@A300-600

SERVICE BULLETIN

(6) Material Effectivity

**CONF 003

MATERIAL QTY PER A/C SEE NOTES

Consumable CMLA01 1

Component COMPA01 2

Component COMPA02 4

Component COMPA03 2

Component COMPA04 2

Component COMPA05 2

Kit 536177A01R00 1

Kit 536177A04R00 1

Kit 536177A07R00 1

Kit 536177A10R00 1

Kit 536177A13R00 1

Kit 536177A16R00 1

Kit 536177A19R00 1

Kit 536177A22R00 1

Kit 536177A25R00 1

Kit 536177A28R00 1

Kit 536177A31R00 1

Kit 536177A34R00 1

**CONF 002

MATERIAL QTY PER A/C SEE NOTES

Consumable CMLA01 1

Component COMPA01 2

Component COMPA02 4

Component COMPA03 2

Component COMPA04 2

Component COMPA05 2

Kit 536177A02R00 1

Kit 536177A05R00 1

Kit 536177A08R00 1

Kit 536177A11R00 1

Kit 536177A14R00 1

Kit 536177A17R00 1

Kit 536177A20R00 1

Kit 536177A23R00 1

Kit 536177A26R00 1

Kit 536177A29R00 1

Kit 536177A32R00 1

Kit 536177A35R00 1

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 4

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@A300-600

SERVICE BULLETIN

**CONF 001

MATERIAL QTY PER A/C SEE NOTES

Consumable CMLA01 1

Component COMPA01 2

Component COMPA02 4

Component COMPA03 2

Component COMPA04 2

Component COMPA05 2

Kit 536177A03R00 1

Kit 536177A06R00 1

Kit 536177A09R00 1

Kit 536177A12R00 1

Kit 536177A15R00 1

Kit 536177A18R00 1

Kit 536177A21R00 1

Kit 536177A24R00 1

Kit 536177A27R00 1

Kit 536177A30R00 1

Kit 536177A33R00 1

Kit 536177A36R00 1

**CONF 004

No Material Set

**CONF ALL

B. CONCURRENT REQUIREMENTS

None

C. REASON

(1) History

During a routine maintenance on A300-600 aircraft, operators have reported separate

instances of cracks in the Frame feet fittings, connecting the Frame lower positions to

the centre wing box (air conditioning bay).

Since this time, AIRBUS has carried out a sampling inspection program on both aircraft

types (A300 and A300-600).

During this sampling program, twenty three A300-600 aircraft were inspected and cracks

were found on the lower Frame fittings of Frame 44 to Frame 46 (LH and RH) on twenty

two of the inspected aircraft. The aircraft with the findings have accumulated between

8000 and 21000 Flight Cycles (FC) and the lengths of the cracks varied between 12 mm

and 18 mm (0.472 in. and 0.709 in.).

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 5

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

SERVICE BULLETIN

Service Bulletin No. A300-53-6111 was created in order to treat the affected areas by

repetitive inspection and also repair in case of crack finding. Repaired Frames were no

longer inspected up to aircraft Limit of Validity (LoV).

Further to new findings on repaired Frame feet, a new detailed Finite Element Model

(FEM) study was performed. Outcomes of this study led Airbus to review the inspection

program.

(2) Objective/Action

The aim of the Service Bulletin, depending of the accomplishment of Service Bulletin No.

A300-53-6111, is to perform a Detailed Inspection (DET) of the lower Frame feet fittings

between Frame 41 and Frame 46 for the entire fleet.

In case of crack finding, two options are possible:

- The cracked Frame foot is replaced by an identical new one and the Inspection

Service Bulletin (ISB) No. A300-53-6177 is still applicable.

- All Frame feet are replaced by new optimized parts as per Modification Service

Bulletin No. A300-53-6176 (Mod. No. 13721S22901). In this case, no further

inspection is necessary.

Any findings (including Nil findings) are to be reported to AIRBUS.

Service Bulletin No. A300-53-6111 is therefore cancelled and superseded by this

new ISB. In addition to this new inspection program, Airbus designed new Frame

feet. Their installation is proposed through a dedicated modification Service Bulletin

No. A300-53-6176. Accomplishment of Modification Service Bulletin No. A300-53-6176

cancels the requirements of this ISB.

(3) Advantages

Accomplishment of this ISB will allow early detection of cracks in order to avoid possible

occurrence of crack propagation which can lead to costly and time-consuming repairs.

(4) Operational/Maintenance Consequences

None

D. DESCRIPTION

To accomplish this Service Bulletin it is necessary to :

**CONF 001

Task 536177-832-801-001: Detailed Inspection of the Frame foot

(1) Do a Detailed Inspection of the Frame Foot at FR41 on LH Side

(2) Do a Detailed Inspection of the Frame Foot at FR41 on RH Side

(3) Do a Detailed Inspection of the Frame Foot at FR42 on LH Side

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 6

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@A300-600

SERVICE BULLETIN

(4) Do a Detailed Inspection of the Frame Foot at FR42 on RH Side

(5) Do a Detailed Inspection of the Frame Foot at FR43 on LH Side

(6) Do a Detailed Inspection of the Frame Foot at FR43 on RH Side

(7) Do a Detailed Inspection of the Frame Foot at FR44 on LH Side

(8) Do a Detailed Inspection of the Frame Foot at FR44 on RH Side

(9) Do a Detailed Inspection of the Frame Foot at FR45 on LH Side

(10) Do a Detailed Inspection of the Frame Foot at FR45 on RH Side

(11) Do a Detailed Inspection of the Frame Foot at FR46 on LH Side

(12) Do a Detailed Inspection of the Frame Foot at FR46 on RH Side

Task 536177-833-801-001: Repair

(1) Depending on Inspection results, if necessary, remove the Fasteners from FR41, LH

side

(2) Depending on Inspection results, remove the Gussets from FR41, LH side

(3) Depending on Inspection results, remove the Frame Foot from FR41, LH side

(4) Depending on Inspection results, install an identical Frame Foot at FR41, LH side

(5) Depending on Inspection results, if removed, install the Fasteners at FR41, LH side

(6) Depending on Inspection results, if necessary, remove the Fasteners from FR41, RH

side

(7) Depending on Inspection results, remove the Gussets from FR41, RH side

(8) Depending on Inspection results, remove the Frame Foot from FR41, RH side

(9) Depending on Inspection results, install an identical Frame Foot at FR41, RH side

(10) Depending on Inspection results, if removed, install the Fasteners at FR41, RH side

(11) Depending on Inspection results, if necessary, remove the Fasteners from FR42,

LH side

(12) Depending on Inspection results, remove the Gussets from FR42, LH side

(13) Depending on Inspection results, remove the Frame Foot from FR42, LH side

(14) Depending on Inspection results, install an identical Frame Foot at FR42, LH side

(15) Depending on Inspection results, if removed, install the Fasteners at FR42, LH side

(16) Depending on Inspection results, if necessary, remove the Fasteners from FR42,

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 7

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

SERVICE BULLETIN

RH side

(17) Depending on Inspection results, remove the Gussets from FR42, RH side

(18) Depending on Inspection results, remove the Frame Foot from FR42, RH side

(19) Depending on Inspection results, install an identical Frame Foot at FR42, RH side

(20) Depending on Inspection results, if removed, install the Fasteners at FR42, RH side

(21) Depending on Inspection results, if necessary, remove the Fasteners from FR43,

LH side

(22) Depending on Inspection results, remove the Gussets from FR43, LH side

(23) Depending on Inspection results, remove the Frame Foot from FR43, LH side

(24) Depending on Inspection results, install an identical Frame Foot at FR43, LH side

(25) Depending on Inspection results, if removed, install the Fasteners at FR43, LH side

(26) Depending on Inspection results, if necessary, remove the Fasteners from FR43,

RH side

(27) Depending on Inspection results, remove the Gussets from FR43, RH side

(28) Depending on Inspection results, remove the Frame Foot from FR43, RH side

(29) Depending on Inspection results, install an identical Frame Foot at FR43, RH side

(30) Depending on Inspection results, if removed, install the Fasteners at FR43, RH side

(31) Depending on Inspection results, if necessary, remove the Fasteners from FR44,

LH side

(32) Depending on Inspection results, remove the Gussets from FR44, LH side

(33) Depending on Inspection results, remove the Frame Foot from FR44, LH side

(34) Depending on Inspection results, install an identical Frame Foot at FR44, LH side

(35) Depending on Inspection results, if removed, install the Fasteners at FR44, LH side

(36) Depending on Inspection results, if necessary, remove the Fasteners from FR44,

RH side

(37) Depending on Inspection results, remove the Gussets from FR44, RH side

(38) Depending on Inspection results, remove the Frame Foot from FR44, RH side

(39) Depending on Inspection results, install an identical Frame Foot at FR44, RH side

(40) Depending on Inspection results, if removed, install the Fasteners at FR44, RH side

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 8

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SERVICE BULLETIN

(41) Depending on Inspection results, if necessary, remove the Fasteners from FR45,

LH side

(42) Depending on Inspection results, remove the Gussets from FR45, LH side

(43) Depending on Inspection results, remove the Frame Foot from FR45, LH side

(44) Depending on Inspection results, install an identical Frame Foot at FR45, LH side

(45) Depending on Inspection results, if removed, install the Fasteners at FR45, LH side

(46) Depending on Inspection results, if necessary, remove the Fasteners from FR45,

RH side

(47) Depending on Inspection results, remove the Gussets from FR45, RH side

(48) Depending on Inspection results, remove the Frame Foot from FR45, RH side

(49) Depending on Inspection results, install an identical Frame Foot at FR45, RH side

(50) Depending on Inspection results, install the Fasteners at FR45, RH side

(51) Depending on Inspection results, if necessary, remove the Fasteners from FR46,

LH side

(52) Depending on Inspection results, remove the Gussets from FR46, LH side

(53) Depending on Inspection results, remove the Frame Foot from FR46, LH side

(54) Depending on Inspection results, install an identical Frame Foot at FR46, LH side

(55) Depending on Inspection results, if removed, install the Fasteners at FR46, LH side

(56) Depending on Inspection results, if necessary, remove the Fasteners from FR46,

RH side

(57) Depending on Inspection results, remove the Gussets from FR46, RH side

(58) Depending on Inspection results, remove the Frame Foot from FR46, RH side

(59) Depending on Inspection results, install an identical Frame Foot at FR46, RH side

(60) Depending on Inspection results, install the Fasteners at FR46, RH side

**CONF 002

Task 536177-832-801-001: Detailed Inspection of the Frame foot

(1) Do a Detailed Inspection of the Frame Foot at FR41 on LH Side

(2) Do a Detailed Inspection of the Frame Foot at FR41 on RH Side

(3) Do a Detailed Inspection of the Frame Foot at FR42 on LH Side

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 9

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SERVICE BULLETIN

(4) Do a Detailed Inspection of the Frame Foot at FR42 on RH Side

(5) Do a Detailed Inspection of the Frame Foot at FR43 on LH Side

(6) Do a Detailed Inspection of the Frame Foot at FR43 on RH Side

(7) Do a Detailed Inspection of the Frame Foot at FR44 on LH Side

(8) Do a Detailed Inspection of the Frame Foot at FR44 on RH Side

(9) Do a Detailed Inspection of the Frame Foot at FR45 on LH Side

(10) Do a Detailed Inspection of the Frame Foot at FR45 on RH Side

(11) Do a Detailed Inspection of the Frame Foot at FR46 on LH Side

(12) Do a Detailed Inspection of the Frame Foot at FR46 on RH Side

Task 536177-833-801-001: Repair

(1) Depending on Inspection results, if necessary, remove the Fasteners from FR41, LH

side

(2) Depending on Inspection results, remove the Gussets from FR41, LH side

(3) Depending on Inspection results, remove the Frame Foot from FR41, LH side

(4) Depending on Inspection results, install an identical Frame Foot at FR41, LH side

(5) Depending on Inspection results, if removed, install the Fasteners at FR41, LH side

(6) Depending on Inspection results, if necessary, remove the Fasteners from FR41, RH

side

(7) Depending on Inspection results, remove the Gussets from FR41, RH side

(8) Depending on Inspection results, remove the Frame Foot from FR41, RH side

(9) Depending on Inspection results, install an identical Frame Foot at FR41, RH side

(10) Depending on Inspection results, if removed, install the Fasteners at FR41, RH side

(11) Depending on Inspection results, if necessary, remove the Fasteners from FR42,

LH side

(12) Depending on Inspection results, remove the Gussets from FR42, LH side

(13) Depending on Inspection results, remove the Frame Foot from FR42, LH side

(14) Depending on Inspection results, install an identical Frame Foot at FR42, LH side

(15) Depending on Inspection results, if removed, install the Fasteners at FR42, LH side

(16) Depending on Inspection results, if necessary, remove the Fasteners from FR42,

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

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

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@A300-600

SERVICE BULLETIN

RH side

(17) Depending on Inspection results, remove the Gussets from FR42, RH side

(18) Depending on Inspection results, remove the Frame Foot from FR42, RH side

(19) Depending on Inspection results, install an identical Frame Foot at FR42, RH side

(20) Depending on Inspection results, if removed, install the Fasteners at FR42, RH side

(21) Depending on Inspection results, if necessary, remove the Fasteners from FR43,

LH side

(22) Depending on Inspection results, remove the Gussets from FR43, LH side

(23) Depending on Inspection results, remove the Frame Foot from FR43, LH side

(24) Depending on Inspection results, install an identical Frame Foot at FR43, LH side

(25) Depending on Inspection results, if removed, install the Fasteners at FR43, LH side

(26) Depending on Inspection results, if necessary, remove the Fasteners from FR43,

RH side

(27) Depending on Inspection results, remove the Gussets from FR43, RH side

(28) Depending on Inspection results, remove the Frame Foot from FR43, RH side

(29) Depending on Inspection results, install an identical Frame Foot at FR43, RH side

(30) Depending on Inspection results, if removed, install the Fasteners at FR43, RH side

(31) Depending on Inspection results, if necessary, remove the Fasteners from FR44,

LH side

(32) Depending on Inspection results, remove the Gussets from FR44, LH side

(33) Depending on Inspection results, remove the Frame Foot from FR44, LH side

(34) Depending on Inspection results, install an identical Frame Foot at FR44, LH side

(35) Depending on Inspection results, if removed, install the Fasteners at FR44, LH side

(36) Depending on Inspection results, if necessary, remove the Fasteners from FR44,

RH side

(37) Depending on Inspection results, remove the Gussets from FR44, RH side

(38) Depending on Inspection results, remove the Frame Foot from FR44, RH side

(39) Depending on Inspection results, install an identical Frame Foot at FR44, RH side

(40) Depending on Inspection results, if removed, install the Fasteners at FR44, RH side

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 11

5

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@A300-600

SERVICE BULLETIN

(41) Depending on Inspection results, if necessary, remove the Fasteners from FR45,

LH side

(42) Depending on Inspection results, remove the Gussets from FR45, LH side

(43) Depending on Inspection results, remove the Frame Foot from FR45, LH side

(44) Depending on Inspection results, install an identical Frame Foot at FR45, LH side

(45) Depending on Inspection results, if removed, install the Fasteners at FR45, LH side

(46) Depending on Inspection results, if necessary, remove the Fasteners from FR45,

RH side

(47) Depending on Inspection results, remove the Gussets from FR45, RH side

(48) Depending on Inspection results, remove the Frame Foot from FR45, RH side

(49) Depending on Inspection results, install an identical Frame Foot at FR45, RH side

(50) Depending on Inspection results, install the Fasteners at FR45, RH side

(51) Depending on Inspection results, if necessary, remove the Fasteners from FR46,

LH side

(52) Depending on Inspection results, remove the Gussets from FR46, LH side

(53) Depending on Inspection results, remove the Frame Foot from FR46, LH side

(54) Depending on Inspection results, install an identical Frame Foot at FR46, LH side

(55) Depending on Inspection results, if removed, install the Fasteners at FR46, LH side

(56) Depending on Inspection results, if necessary, remove the Fasteners from FR46,

RH side

(57) Depending on Inspection results, remove the Gussets from FR46, RH side

(58) Depending on Inspection results, remove the Frame Foot from FR46, RH side

(59) Depending on Inspection results, install an identical Frame Foot at FR46, RH side

(60) Depending on Inspection results, install the Fasteners at FR46, RH side

**CONF 003

Task 536177-832-801-001: Detailed Inspection of the Frame foot

(1) Do a Detailed Inspection of the Frame Foot at FR41 on LH Side

(2) Do a Detailed Inspection of the Frame Foot at FR41 on RH Side

(3) Do a Detailed Inspection of the Frame Foot at FR42 on LH Side

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 12

5

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@A300-600

SERVICE BULLETIN

(4) Do a Detailed Inspection of the Frame Foot at FR42 on RH Side

(5) Do a Detailed Inspection of the Frame Foot at FR43 on LH Side

(6) Do a Detailed Inspection of the Frame Foot at FR43 on RH Side

(7) Do a Detailed Inspection of the Frame Foot at FR44 on LH Side

(8) Do a Detailed Inspection of the Frame Foot at FR44 on RH Side

(9) Do a Detailed Inspection of the Frame Foot at FR45 on LH Side

(10) Do a Detailed Inspection of the Frame Foot at FR45 on RH Side

(11) Do a Detailed Inspection of the Frame Foot at FR46 on LH Side

(12) Do a Detailed Inspection of the Frame Foot at FR46 on RH Side

Task 536177-833-801-001: Repair

(1) Depending on Inspection results, if necessary, remove the Fasteners from FR41, LH

side

(2) Depending on Inspection results, remove the Gussets from FR41, LH side

(3) Depending on Inspection results, remove the Frame Foot from FR41, LH side

(4) Depending on Inspection results, install an identical Frame Foot at FR41, LH side

(5) Depending on Inspection results, if removed, install the Fasteners at FR41, LH side

(6) Depending on Inspection results, if necessary, remove the Fasteners from FR41, RH

side

(7) Depending on Inspection results, remove the Gussets from FR41, RH side

(8) Depending on Inspection results, remove the Frame Foot from FR41, RH side

(9) Depending on Inspection results, install an identical Frame Foot at FR41, RH side

(10) Depending on Inspection results, if removed, install the Fasteners at FR41, RH side

(11) Depending on Inspection results, if necessary, remove the Fasteners from FR42,

LH side

(12) Depending on Inspection results, remove the Gussets from FR42, LH side

(13) Depending on Inspection results, remove the Frame Foot from FR42, LH side

(14) Depending on Inspection results, install an identical Frame Foot at FR42, LH side

(15) Depending on Inspection results, if removed, install the Fasteners at FR42, LH side

(16) Depending on Inspection results, if necessary, remove the Fasteners from FR42,

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 13

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@A300-600

SERVICE BULLETIN

RH side

(17) Depending on Inspection results, remove the Gussets from FR42, RH side

(18) Depending on Inspection results, remove the Frame Foot from FR42, RH side

(19) Depending on Inspection results, install an identical Frame Foot at FR42, RH side

(20) Depending on Inspection results, if removed, install the Fasteners at FR42, RH side

(21) Depending on Inspection results, if necessary, remove the Fasteners from FR43,

LH side

(22) Depending on Inspection results, remove the Gussets from FR43, LH side

(23) Depending on Inspection results, remove the Frame Foot from FR43, LH side

(24) Depending on Inspection results, install an identical Frame Foot at FR43, LH side

(25) Depending on Inspection results, if removed, install the Fasteners at FR43, LH side

(26) Depending on Inspection results, if necessary, remove the Fasteners from FR43,

RH side

(27) Depending on Inspection results, remove the Gussets from FR43, RH side

(28) Depending on Inspection results, remove the Frame Foot from FR43, RH side

(29) Depending on Inspection results, install an identical Frame Foot at FR43, RH side

(30) Depending on Inspection results, if removed, install the Fasteners at FR43, RH side

(31) Depending on Inspection results, if necessary, remove the Fasteners from FR44,

LH side

(32) Depending on Inspection results, remove the Gussets from FR44, LH side

(33) Depending on Inspection results, remove the Frame Foot from FR44, LH side

(34) Depending on Inspection results, install an identical Frame Foot at FR44, LH side

(35) Depending on Inspection results, if removed, install the Fasteners at FR44, LH side

(36) Depending on Inspection results, if necessary, remove the Fasteners from FR44,

RH side

(37) Depending on Inspection results, remove the Gussets from FR44, RH side

(38) Depending on Inspection results, remove the Frame Foot from FR44, RH side

(39) Depending on Inspection results, install an identical Frame Foot at FR44, RH side

(40) Depending on Inspection results, if removed, install the Fasteners at FR44, RH side

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 14

5

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@A300-600

SERVICE BULLETIN

(41) Depending on Inspection results, if necessary, remove the Fasteners from FR45,

LH side

(42) Depending on Inspection results, remove the Gussets from FR45, LH side

(43) Depending on Inspection results, remove the Frame Foot from FR45, LH side

(44) Depending on Inspection results, install an identical Frame Foot at FR45, LH side

(45) Depending on Inspection results, if removed, install the Fasteners at FR45, LH side

(46) Depending on Inspection results, if necessary, remove the Fasteners from FR45,

RH side

(47) Depending on Inspection results, remove the Gussets from FR45, RH side

(48) Depending on Inspection results, remove the Frame Foot from FR45, RH side

(49) Depending on Inspection results, install an identical Frame Foot at FR45, RH side

(50) Depending on Inspection results, install the Fasteners at FR45, RH side

(51) Depending on Inspection results, if necessary, remove the Fasteners from FR46,

LH side

(52) Depending on Inspection results, remove the Gussets from FR46, LH side

(53) Depending on Inspection results, remove the Frame Foot from FR46, LH side

(54) Depending on Inspection results, install an identical Frame Foot at FR46, LH side

(55) Depending on Inspection results, if removed, install the Fasteners at FR46, LH side

(56) Depending on Inspection results, if necessary, remove the Fasteners from FR46,

RH side

(57) Depending on Inspection results, remove the Gussets from FR46, RH side

(58) Depending on Inspection results, remove the Frame Foot from FR46, RH side

(59) Depending on Inspection results, install an identical Frame Foot at FR46, RH side

(60) Depending on Inspection results, install the Fasteners at FR46, RH side

**CONF 004

Task 536177-839-801-001: Contact and Report to AIRBUS

(1) Contact and Report to AIRBUS

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 15

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@A300-600

SERVICE BULLETIN

**CONF ALL

E. COMPLIANCE

(1) Classification

MANDATORY: Service Bulletin must be accomplished.

(2) Accomplishment Timescale

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

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

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

intervals given but reference should be made to the AD for confirmation of the mandated

accomplishment timescale.

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 16

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@A300-600

SERVICE BULLETIN

Table 1, Config. 001 - Detailed Inspection of the Frame foot

Compliance time (Whichever

occurs later)

Condition Action

Threshold

(Whichever

occurs first)

Grace period

(Whichever

occurs first)

Repetitive

interval

(Whichever

occurs first)

Frame foot not

inspected as

per Service

Bulletin No.

A300-53-6111

- For

aircraft (A/C)

with Average

Flight Time

(AFT) higher

than 1.5

hours:

5000 Flight

Cycles (FC) /

10800 Flight

Hours (FH)

- For A/C with

AFT lower or

equal to 1.5

hours:

5400 FC /

8100 FH

1000 FC from

issuance of

revision 04 of

Service Bulletin

No.

A300-53-6111

All Frame feet None

Frame foot

inspected as

per Service

Bulletin No.

A300-53-6111

with nil finding

and thus not

repaired

Do a detailed

inspection of

the area 1 and

the area 2 of

the Frame foot

in accordance

with TASK

536177-832-801

001

- For A/C with

AFT higher

than 1.5

hours:

3200 FC

/ 7000 FH

from last

inspection as

per Service

Bulletin No.

A300-53-6111

- For A/C with

AFT lower or

equal to 1.5

hours:

3500 FC

/ 5300 FH

from last

inspection as

per Service

Bulletin No.

A300-53-6111

None None

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 17

5

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@A300-600

SERVICE BULLETIN

Table 1, Config. 001 - Detailed Inspection of the Frame foot

Compliance time (Whichever

occurs later)

Condition Action

Threshold

(Whichever

occurs first)

Grace period

(Whichever

occurs first)

Repetitive

interval

(Whichever

occurs first)

Apply Service

Bulletin No.

A300-53-6176

See NOTE (**)

And

Before next

flight

None None

Send inspection

report to

AIRBUS

And

1 month from

inspection date

None None

No further

action

None None None

OR

Replace the

cracked Frame

foot by a new

identical one in

accordance

with TASK

536177-833-801

001

And

Before next

flight

None None

Send inspection

report to

AIRBUS

And

1 month from

inspection date

None None

Crack found in area 1 or area 2

See NOTE (*)

Repeat the

inspection of

the replaced

Frame foot in

accordance

with TASK

536177-832-801

001

- For A/C with

AFT higher

than 1.5

hours:

5000 FC

/ 10800

FH from

Frame foot

replacement

- For A/C with

AFT lower or

equal to 1.5

hours:

5400 FC /

8100 FH from

Frame foot

replacement

None - For A/C with

AFT higher

than 1.5

hours:

3200 FC /

7000 FH from

Frame foot

replacement

- For A/C with

AFT lower or

equal to 1.5

hours:

3500 FC /

5300 FH from

Frame foot

replacement

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 18

5

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

SERVICE BULLETIN

Table 1, Config. 001 - Detailed Inspection of the Frame foot

Compliance time (Whichever

occurs later)

Condition Action

Threshold

(Whichever

occurs first)

Grace period

(Whichever

occurs first)

Repetitive

interval

(Whichever

occurs first)

Apply Service

Bulletin No.

A300-53-6176

See NOTE (**)

And

Before next

flight

None None

Send inspection

report to

AIRBUS

And

1 month from

inspection date

None None

No further

action

None None None

OR

Send inspection

report to

AIRBUS

And

1 month from

inspection date

None None

No crack found in area 1 nor in

area 2

Repeat the

inspection of

the Frame foot

in accordance

with TASK

536177-832-801

001

None None - For A/C with

AFT higher

than 1.5

hours: 3200

FC / 7000 FH

- For A/C with

AFT lower or

equal to 1.5

hours:

3500 FC /

5300 FH

NOTE (*): If a crack is longer than 30 mm (1.181 in.), inform AIRBUS and send the affected Frame

foot for laboratory investigation

NOTE (**): The accomplishment of the Service Bulletin No. A300-53-6176 consists in replacing all the

Frame feet (between Frame 41 and Frame 46, LH and RH sides) of the aircraft with optimized Frame

feet.

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 19

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@A300-600

SERVICE BULLETIN

Table 2, Config. 002 - Detailed Inspection of the Frame foot

Compliance time (Whichever occurs

later)

Condition Action

Threshold

(Whichever occurs

first)

Grace period

(Whichever occurs

first)

Repetitive interval

(Whichever occurs

first)

All Frame feet Do a detailed

inspection of the

area 1 and the

area 2 of the

Frame foot in

accordance with

TASK

536177-832-801

001

- For aircraft (A/C)

with AFT higher

than 1.5 hours:

3200 FC /

7000 FH from

Frame foot repair

embodiment

- For A/C with AFT

lower or equal to

1.5 hours:

3500 FC /

5300 FH from

Frame foot repair

embodiment

1000 FC from

issuance of

Service Bulletin

No. A300-53-6177

None

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 20

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@A300-600

SERVICE BULLETIN

Table 2, Config. 002 - Detailed Inspection of the Frame foot

Compliance time (Whichever occurs

later)

Condition Action

Threshold

(Whichever occurs

first)

Grace period

(Whichever occurs

first)

Repetitive interval

(Whichever occurs

first)

Apply Service

Bulletin No.

A300-53-6176

See NOTE (**)

And

Before next flight None None

Send inspection

report to AIRBUS

And

1 month from

inspection date

None None

No further action None None None

OR

Replace the

cracked Frame foot

by a new identical

one and do the

cutting-out in

accordance with

TASK

536177-833-801

001

And

Before next flight None None

Send inspection

report to AIRBUS

And

1 month from

inspection date

None None

Crack found in

area 1 or area 2

See NOTE (*)

Repeat the

inspection of the

replaced Frame

foot in accordance

with TASK

536177-832-801

001

- For A/C with AFT

higher than 1.5

hours:

5000 FC / 10800

FH from Frame

foot replacement

- For A/C with AFT

lower or equal to

1.5 hours:

5400 FC / 8100

FH from Frame

foot replacement

None - For A/C with AFT

higher than 1.5

hours:

3200 FC / 7000

FH from Frame

foot replacement

- For A/C with AFT

lower or equal to

1.5 hours:

3500 FC / 5300

FH from Frame

foot replacement

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 21

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SERVICE BULLETIN

Table 2, Config. 002 - Detailed Inspection of the Frame foot

Compliance time (Whichever occurs

later)

Condition Action

Threshold

(Whichever occurs

first)

Grace period

(Whichever occurs

first)

Repetitive interval

(Whichever occurs

first)

Apply Service

Bulletin No.

A300-53-6176

See NOTE (**)

And

Before next flight None None

Send inspection

report to AIRBUS

And

1 month from

inspection date

None None

No further action None None None

OR

Send inspection

report to AIRBUS

And

1 month from

inspection date

None None

No crack found in

area 1 nor in area

2

Repeat the

inspection of the

Frame foot in

accordance with

TASK

536177-832-801

001

None None - For A/C with AFT

higher than 1.5

hours: 3200 FC /

7000 FH

- For A/C with AFT

lower or equal to

1.5 hours:

3500 FC / 5300

FH

NOTE (*): If a crack is longer than 30 mm (1.181 in.), inform AIRBUS and send the affected Frame

foot for laboratory investigation

NOTE (**): The accomplishment of the Service Bulletin No. A300-53-6176 consists in replacing all the

Frame feet (between Frame 41 and Frame 46, LH and RH sides) of the aircraft with optimized Frame

feet.

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 22

5

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@A300-600

SERVICE BULLETIN

Table 3, Config. 003 - Detailed Inspection of the Frame foot

Compliance time (Whichever occurs

later)

Condition Action

Threshold

(Whichever occurs

first)

Grace period

(Whichever occurs

first)

Repetitive interval

(Whichever occurs

first)

All Frame feet Do a detailed

inspection of the

area 2 of the

Frame foot in

accordance with

TASK

536177-832-801

001

- For aircraft (A/C)

with AFT higher

than 1.5 hours:

3200 FC /

7000 FH from

Frame foot repair

embodiment

- For A/C with AFT

lower or equal to

1.5 hours:

3500 FC /

5300 FH from

Frame foot repair

embodiment

1000 FC from

issuance of

Service Bulletin

No. A300-53-6177

None

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 23

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@A300-600

SERVICE BULLETIN

Table 3, Config. 003 - Detailed Inspection of the Frame foot

Compliance time (Whichever occurs

later)

Condition Action

Threshold

(Whichever occurs

first)

Grace period

(Whichever occurs

first)

Repetitive interval

(Whichever occurs

first)

Apply Service

Bulletin No.

A300-53-6176

See NOTE (**)

And

Before next flight None None

Send inspection

report to AIRBUS

And

1 month from

inspection date

None None

No further action None None None

OR

Replace the

cracked Frame foot

by a new identical

one and do the

cutting-out in

accordance with

TASK

536177-833-801

001

And

Before next flight None None

Send inspection

report to AIRBUS

And

1 month from

inspection date

None None

Crack found in

area 2

See NOTE (*)

Repeat the

inspection of the

replaced Frame

foot, in accordance

with TASK

536177-832-801

001

- For A/C with AFT

higher than 1.5

hours:

5000 FC / 10800

FH from Frame

foot replacement

- For A/C with AFT

lower or equal to

1.5 hours:

5400 FC / 8100

FH from Frame

foot replacement

None - For A/C with AFT

higher than 1.5

hours:

3200 FC / 7000

FH from Frame

foot replacement

- For A/C with AFT

lower or equal to

1.5 hours:

3500 FC / 5300

FH from Frame

foot replacement

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 24

5

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

SERVICE BULLETIN

Table 3, Config. 003 - Detailed Inspection of the Frame foot

Compliance time (Whichever occurs

later)

Condition Action

Threshold

(Whichever occurs

first)

Grace period

(Whichever occurs

first)

Repetitive interval

(Whichever occurs

first)

Apply Service

Bulletin No.

A300-53-6176

See NOTE (**)

And

Before next flight None None

Send inspection

report to AIRBUS

And

1 month from

inspection date

None None

No further action None None None

OR

Send inspection

report to AIRBUS

And

1 month from

inspection date

None None

No crack found in

area 2

Repeat the

inspection of the

Frame foot in

accordance with

TASK

536177-832-801

001

None None - For A/C with AFT

higher than 1.5

hours: 3200 FC /

7000 FH

- For A/C with AFT

lower or equal to

1.5 hours:

3500 FC / 5300

FH

NOTE (*): If a crack is longer than 30 mm (1.181 in.), inform AIRBUS and send the affected Frame

foot for laboratory investigation

NOTE (**): The accomplishment of the Service Bulletin No. A300-53-6176 consists in replacing all the

Frame feet (between Frame 41 and Frame 46, LH and RH sides) of the aircraft with optimized Frame

feet.

Table 4, Config. 004 - Contact and Report to AIRBUS

Compliance time (Whichever occurs

later)

Condition Action

Threshold

(Whichever occurs

first)

Grace period

(Whichever occurs

first)

Repetitive interval

(Whichever occurs

first)

All Frame feet Contact and report

to AIRBUS in

accordance with

TASK

536177-839-801

001

6 months from this

Service Bulletin

issuance

None None

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 25

5

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

SERVICE BULLETIN

F. APPROVAL

The technical content of this document is approved under the authority of Design

Organisation Approval No. EASA.21J.031.

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

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

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

before incorporation of the Service Bulletin.

G. MANPOWER

The manpower estimates given in this Service Bulletin are based on the direct labor cost to

do the work. These estimates assume that the work will be done by experienced personnel,

and may need to be revised upwards to suit operator’s circumstances. The estimates do not

include the time to prepare, plan or inspect the work. Manufacture and procurement of parts

and tools, drying times for paints, sealants, etc., and general administration work are also not

included.

**CONF 001

Task 536177-832-801-001: Detailed Inspection of the Frame foot

Get Access 1.00

On Aircraft

Do a Detailed Inspection of the Frame Foot at FR41 on

LH Side

0.50

Do a Detailed Inspection of the Frame Foot at FR41 on

RH Side

0.50

Do a Detailed Inspection of the Frame Foot at FR42 on

LH Side

0.50

Do a Detailed Inspection of the Frame Foot at FR42 on

RH Side

0.50

Do a Detailed Inspection of the Frame Foot at FR43 on

LH Side

0.50

Do a Detailed Inspection of the Frame Foot at FR43 on

RH Side

0.50

Do a Detailed Inspection of the Frame Foot at FR44 on

LH Side

0.50

Do a Detailed Inspection of the Frame Foot at FR44 on

RH Side

0.50

Do a Detailed Inspection of the Frame Foot at FR45 on

LH Side

0.50

Do a Detailed Inspection of the Frame Foot at FR45 on

RH Side

0.50

Do a Detailed Inspection of the Frame Foot at FR46 on

LH Side

0.50

Do a Detailed Inspection of the Frame Foot at FR46 on

RH Side

0.50

Close-Up 1.00

TOTAL MANHOURS 8.00

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 26

5

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

SERVICE BULLETIN

Task 536177-832-801-001: Detailed Inspection of the Frame foot

ELAPSED TIME (HOURS) 2.50

Task 536177-833-801-001: Repair

Get Access 12.00

On Aircraft

Depending on Inspection results, if necessary, remove

the Fasteners from FR41, LH side

4.00

Depending on Inspection results, remove the Gussets

from FR41, LH side

1.00

Depending on Inspection results, remove the Frame

Foot from FR41, LH side

16.00

Depending on Inspection results, install an identical

Frame Foot at FR41, LH side

16.00

Depending on Inspection results, if removed, install the

Fasteners at FR41, LH side

6.00

Depending on Inspection results, if necessary, remove

the Fasteners from FR41, RH side

4.00

Depending on Inspection results, remove the Gussets

from FR41, RH side

1.00

Depending on Inspection results, remove the Frame

Foot from FR41, RH side

16.00

Depending on Inspection results, install an identical

Frame Foot at FR41, RH side

16.00

Depending on Inspection results, if removed, install the

Fasteners at FR41, RH side

6.00

Depending on Inspection results, if necessary, remove

the Fasteners from FR42, LH side

4.00

Depending on Inspection results, remove the Gussets

from FR42, LH side

1.00

Depending on Inspection results, remove the Frame

Foot from FR42, LH side

16.00

Depending on Inspection results, install an identical

Frame Foot at FR42, LH side

16.00

Depending on Inspection results, if removed, install the

Fasteners at FR42, LH side

6.00

Depending on Inspection results, if necessary, remove

the Fasteners from FR42, RH side

4.00

Depending on Inspection results, remove the Gussets

from FR42, RH side

1.00

Depending on Inspection results, remove the Frame

Foot from FR42, RH side

16.00

Depending on Inspection results, install an identical

Frame Foot at FR42, RH side

16.00

Depending on Inspection results, if removed, install the

Fasteners at FR42, RH side

6.00

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 27

5

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

SERVICE BULLETIN

Task 536177-833-801-001: Repair

Depending on Inspection results, if necessary, remove

the Fasteners from FR43, LH side

4.00

Depending on Inspection results, remove the Gussets

from FR43, LH side

1.00

Depending on Inspection results, remove the Frame

Foot from FR43, LH side

16.00

Depending on Inspection results, install an identical

Frame Foot at FR43, LH side

16.00

Depending on Inspection results, if removed, install the

Fasteners at FR43, LH side

6.00

Depending on Inspection results, if necessary, remove

the Fasteners from FR43, RH side

4.00

Depending on Inspection results, remove the Gussets

from FR43, RH side

1.00

Depending on Inspection results, remove the Frame

Foot from FR43, RH side

16.00

Depending on Inspection results, install an identical

Frame Foot at FR43, RH side

16.00

Depending on Inspection results, if removed, install the

Fasteners at FR43, RH side

6.00

Depending on Inspection results, if necessary, remove

the Fasteners from FR44, LH side

4.00

Depending on Inspection results, remove the Gussets

from FR44, LH side

1.00

Depending on Inspection results, remove the Frame

Foot from FR44, LH side

16.00

Depending on Inspection results, install an identical

Frame Foot at FR44, LH side

16.00

Depending on Inspection results, if removed, install the

Fasteners at FR44, LH side

6.00

Depending on Inspection results, if necessary, remove

the Fasteners from FR44, RH side

4.00

Depending on Inspection results, remove the Gussets

from FR44, RH side

1.00

Depending on Inspection results, remove the Frame

Foot from FR44, RH side

16.00

Depending on Inspection results, install an identical

Frame Foot at FR44, RH side

16.00

Depending on Inspection results, if removed, install the

Fasteners at FR44, RH side

6.00

Depending on Inspection results, if necessary, remove

the Fasteners from FR45, LH side

4.00

Depending on Inspection results, remove the Gussets

from FR45, LH side

1.00

Depending on Inspection results, remove the Frame

Foot from FR45, LH side

16.00

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 28

5

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

SERVICE BULLETIN

Task 536177-833-801-001: Repair

Depending on Inspection results, install an identical

Frame Foot at FR45, LH side

16.00

Depending on Inspection results, if removed, install the

Fasteners at FR45, LH side

6.00

Depending on Inspection results, if necessary, remove

the Fasteners from FR45, RH side

4.00

Depending on Inspection results, remove the Gussets

from FR45, RH side

1.00

Depending on Inspection results, remove the Frame

Foot from FR45, RH side

16.00

Depending on Inspection results, install an identical

Frame Foot at FR45, RH side

16.00

Depending on Inspection results, install the Fasteners

at FR45, RH side

6.00

Depending on Inspection results, if necessary, remove

the Fasteners from FR46, LH side

4.00

Depending on Inspection results, remove the Gussets

from FR46, LH side

1.00

Depending on Inspection results, remove the Frame

Foot from FR46, LH side

16.00

Depending on Inspection results, install an identical

Frame Foot at FR46, LH side

16.00

Depending on Inspection results, if removed, install the

Fasteners at FR46, LH side

6.00

Depending on Inspection results, if necessary, remove

the Fasteners from FR46, RH side

4.00

Depending on Inspection results, remove the Gussets

from FR46, RH side

1.00

Depending on Inspection results, remove the Frame

Foot from FR46, RH side

16.00

Depending on Inspection results, install an identical

Frame Foot at FR46, RH side

16.00

Depending on Inspection results, install the Fasteners

at FR46, RH side

6.00

Close-Up 13.00

TOTAL MANHOURS 541.00

ELAPSED TIME (HOURS) 42.00

NOTE: For an explanation of the manhours and elapsed time, refer to the Gantt

Chart, Fig. A-FAAAA given in Appendix 01 - Elapsed Time Assumptions .

NOTE: The minimum manhours necessary to accomplish this Service Bulletin are

those for the Inspection. Depending on the inspection result, additional

manhours can apply.

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 29

5

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

SERVICE BULLETIN

**CONF 002

Task 536177-832-801-001: Detailed Inspection of the Frame foot

Get Access 1.00

On Aircraft

Do a Detailed Inspection of the Frame Foot at FR41 on

LH Side

0.50

Do a Detailed Inspection of the Frame Foot at FR41 on

RH Side

0.50

Do a Detailed Inspection of the Frame Foot at FR42 on

LH Side

0.50

Do a Detailed Inspection of the Frame Foot at FR42 on

RH Side

0.50

Do a Detailed Inspection of the Frame Foot at FR43 on

LH Side

0.50

Do a Detailed Inspection of the Frame Foot at FR43 on

RH Side

0.50

Do a Detailed Inspection of the Frame Foot at FR44 on

LH Side

0.50

Do a Detailed Inspection of the Frame Foot at FR44 on

RH Side

0.50

Do a Detailed Inspection of the Frame Foot at FR45 on

LH Side

0.50

Do a Detailed Inspection of the Frame Foot at FR45 on

RH Side

0.50

Do a Detailed Inspection of the Frame Foot at FR46 on

LH Side

0.50

Do a Detailed Inspection of the Frame Foot at FR46 on

RH Side

0.50

Close-Up 1.00

TOTAL MANHOURS 8.00

ELAPSED TIME (HOURS) 2.50

Task 536177-833-801-001: Repair

Get Access 12.00

On Aircraft

Depending on Inspection results, if necessary, remove

the Fasteners from FR41, LH side

4.00

Depending on Inspection results, remove the Gussets

from FR41, LH side

1.00

Depending on Inspection results, remove the Frame

Foot from FR41, LH side

16.00

Depending on Inspection results, install an identical

Frame Foot at FR41, LH side

16.00

Depending on Inspection results, if removed, install the

Fasteners at FR41, LH side

6.00

Depending on Inspection results, if necessary, remove

the Fasteners from FR41, RH side

4.00

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 30

5

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

SERVICE BULLETIN

Task 536177-833-801-001: Repair

Depending on Inspection results, remove the Gussets

from FR41, RH side

1.00

Depending on Inspection results, remove the Frame

Foot from FR41, RH side

16.00

Depending on Inspection results, install an identical

Frame Foot at FR41, RH side

16.00

Depending on Inspection results, if removed, install the

Fasteners at FR41, RH side

6.00

Depending on Inspection results, if necessary, remove

the Fasteners from FR42, LH side

4.00

Depending on Inspection results, remove the Gussets

from FR42, LH side

1.00

Depending on Inspection results, remove the Frame

Foot from FR42, LH side

16.00

Depending on Inspection results, install an identical

Frame Foot at FR42, LH side

16.00

Depending on Inspection results, if removed, install the

Fasteners at FR42, LH side

6.00

Depending on Inspection results, if necessary, remove

the Fasteners from FR42, RH side

4.00

Depending on Inspection results, remove the Gussets

from FR42, RH side

1.00

Depending on Inspection results, remove the Frame

Foot from FR42, RH side

16.00

Depending on Inspection results, install an identical

Frame Foot at FR42, RH side

16.00

Depending on Inspection results, if removed, install the

Fasteners at FR42, RH side

6.00

Depending on Inspection results, if necessary, remove

the Fasteners from FR43, LH side

4.00

Depending on Inspection results, remove the Gussets

from FR43, LH side

1.00

Depending on Inspection results, remove the Frame

Foot from FR43, LH side

16.00

Depending on Inspection results, install an identical

Frame Foot at FR43, LH side

16.00

Depending on Inspection results, if removed, install the

Fasteners at FR43, LH side

6.00

Depending on Inspection results, if necessary, remove

the Fasteners from FR43, RH side

4.00

Depending on Inspection results, remove the Gussets

from FR43, RH side

1.00

Depending on Inspection results, remove the Frame

Foot from FR43, RH side

16.00

Depending on Inspection results, install an identical

Frame Foot at FR43, RH side

16.00

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 31

5

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

SERVICE BULLETIN

Task 536177-833-801-001: Repair

Depending on Inspection results, if removed, install the

Fasteners at FR43, RH side

6.00

Depending on Inspection results, if necessary, remove

the Fasteners from FR44, LH side

4.00

Depending on Inspection results, remove the Gussets

from FR44, LH side

1.00

Depending on Inspection results, remove the Frame

Foot from FR44, LH side

16.00

Depending on Inspection results, install an identical

Frame Foot at FR44, LH side

16.00

Depending on Inspection results, if removed, install the

Fasteners at FR44, LH side

6.00

Depending on Inspection results, if necessary, remove

the Fasteners from FR44, RH side

4.00

Depending on Inspection results, remove the Gussets

from FR44, RH side

1.00

Depending on Inspection results, remove the Frame

Foot from FR44, RH side

16.00

Depending on Inspection results, install an identical

Frame Foot at FR44, RH side

16.00

Depending on Inspection results, if removed, install the

Fasteners at FR44, RH side

6.00

Depending on Inspection results, if necessary, remove

the Fasteners from FR45, LH side

4.00

Depending on Inspection results, remove the Gussets

from FR45, LH side

1.00

Depending on Inspection results, remove the Frame

Foot from FR45, LH side

16.00

Depending on Inspection results, install an identical

Frame Foot at FR45, LH side

16.00

Depending on Inspection results, if removed, install the

Fasteners at FR45, LH side

6.00

Depending on Inspection results, if necessary, remove

the Fasteners from FR45, RH side

4.00

Depending on Inspection results, remove the Gussets

from FR45, RH side

1.00

Depending on Inspection results, remove the Frame

Foot from FR45, RH side

16.00

Depending on Inspection results, install an identical

Frame Foot at FR45, RH side

16.00

Depending on Inspection results, install the Fasteners

at FR45, RH side

6.00

Depending on Inspection results, if necessary, remove

the Fasteners from FR46, LH side

4.00

Depending on Inspection results, remove the Gussets

from FR46, LH side

1.00

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 32

5

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

SERVICE BULLETIN

Task 536177-833-801-001: Repair

Depending on Inspection results, remove the Frame

Foot from FR46, LH side

16.00

Depending on Inspection results, install an identical

Frame Foot at FR46, LH side

16.00

Depending on Inspection results, if removed, install the

Fasteners at FR46, LH side

6.00

Depending on Inspection results, if necessary, remove

the Fasteners from FR46, RH side

4.00

Depending on Inspection results, remove the Gussets

from FR46, RH side

1.00

Depending on Inspection results, remove the Frame

Foot from FR46, RH side

16.00

Depending on Inspection results, install an identical

Frame Foot at FR46, RH side

16.00

Depending on Inspection results, install the Fasteners

at FR46, RH side

6.00

Close-Up 13.00

TOTAL MANHOURS 541.00

ELAPSED TIME (HOURS) 42.00

NOTE: For an explanation of the manhours and elapsed time, refer to the Gantt

Chart, Fig. A-FAAAA given in Appendix 01 - Elapsed Time Assumptions .

NOTE: The minimum manhours necessary to accomplish this Service Bulletin are

those for the Inspection. Depending on the inspection result, additional

manhours can apply.

**CONF 003

Task 536177-832-801-001: Detailed Inspection of the Frame foot

Get Access 1.00

On Aircraft

Do a Detailed Inspection of the Frame Foot at FR41 on

LH Side

0.50

Do a Detailed Inspection of the Frame Foot at FR41 on

RH Side

0.50

Do a Detailed Inspection of the Frame Foot at FR42 on

LH Side

0.50

Do a Detailed Inspection of the Frame Foot at FR42 on

RH Side

0.50

Do a Detailed Inspection of the Frame Foot at FR43 on

LH Side

0.50

Do a Detailed Inspection of the Frame Foot at FR43 on

RH Side

0.50

Do a Detailed Inspection of the Frame Foot at FR44 on

LH Side

0.50

Do a Detailed Inspection of the Frame Foot at FR44 on

RH Side

0.50

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 33

5

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

SERVICE BULLETIN

Task 536177-832-801-001: Detailed Inspection of the Frame foot

Do a Detailed Inspection of the Frame Foot at FR45 on

LH Side

0.50

Do a Detailed Inspection of the Frame Foot at FR45 on

RH Side

0.50

Do a Detailed Inspection of the Frame Foot at FR46 on

LH Side

0.50

Do a Detailed Inspection of the Frame Foot at FR46 on

RH Side

0.50

Close-Up 1.00

TOTAL MANHOURS 8.00

ELAPSED TIME (HOURS) 2.50

Task 536177-833-801-001: Repair

Get Access 12.00

On Aircraft

Depending on Inspection results, if necessary, remove

the Fasteners from FR41, LH side

4.00

Depending on Inspection results, remove the Gussets

from FR41, LH side

1.00

Depending on Inspection results, remove the Frame

Foot from FR41, LH side

16.00

Depending on Inspection results, install an identical

Frame Foot at FR41, LH side

16.00

Depending on Inspection results, if removed, install the

Fasteners at FR41, LH side

6.00

Depending on Inspection results, if necessary, remove

the Fasteners from FR41, RH side

4.00

Depending on Inspection results, remove the Gussets

from FR41, RH side

1.00

Depending on Inspection results, remove the Frame

Foot from FR41, RH side

16.00

Depending on Inspection results, install an identical

Frame Foot at FR41, RH side

16.00

Depending on Inspection results, if removed, install the

Fasteners at FR41, RH side

6.00

Depending on Inspection results, if necessary, remove

the Fasteners from FR42, LH side

4.00

Depending on Inspection results, remove the Gussets

from FR42, LH side

1.00

Depending on Inspection results, remove the Frame

Foot from FR42, LH side

16.00

Depending on Inspection results, install an identical

Frame Foot at FR42, LH side

16.00

Depending on Inspection results, if removed, install the

Fasteners at FR42, LH side

6.00

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 34

5

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

SERVICE BULLETIN

Task 536177-833-801-001: Repair

Depending on Inspection results, if necessary, remove

the Fasteners from FR42, RH side

4.00

Depending on Inspection results, remove the Gussets

from FR42, RH side

1.00

Depending on Inspection results, remove the Frame

Foot from FR42, RH side

16.00

Depending on Inspection results, install an identical

Frame Foot at FR42, RH side

16.00

Depending on Inspection results, if removed, install the

Fasteners at FR42, RH side

6.00

Depending on Inspection results, if necessary, remove

the Fasteners from FR43, LH side

4.00

Depending on Inspection results, remove the Gussets

from FR43, LH side

1.00

Depending on Inspection results, remove the Frame

Foot from FR43, LH side

16.00

Depending on Inspection results, install an identical

Frame Foot at FR43, LH side

16.00

Depending on Inspection results, if removed, install the

Fasteners at FR43, LH side

6.00

Depending on Inspection results, if necessary, remove

the Fasteners from FR43, RH side

4.00

Depending on Inspection results, remove the Gussets

from FR43, RH side

1.00

Depending on Inspection results, remove the Frame

Foot from FR43, RH side

16.00

Depending on Inspection results, install an identical

Frame Foot at FR43, RH side

16.00

Depending on Inspection results, if removed, install the

Fasteners at FR43, RH side

6.00

Depending on Inspection results, if necessary, remove

the Fasteners from FR44, LH side

4.00

Depending on Inspection results, remove the Gussets

from FR44, LH side

1.00

Depending on Inspection results, remove the Frame

Foot from FR44, LH side

16.00

Depending on Inspection results, install an identical

Frame Foot at FR44, LH side

16.00

Depending on Inspection results, if removed, install the

Fasteners at FR44, LH side

6.00

Depending on Inspection results, if necessary, remove

the Fasteners from FR44, RH side

4.00

Depending on Inspection results, remove the Gussets

from FR44, RH side

1.00

Depending on Inspection results, remove the Frame

Foot from FR44, RH side

16.00

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 35

5

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

SERVICE BULLETIN

Task 536177-833-801-001: Repair

Depending on Inspection results, install an identical

Frame Foot at FR44, RH side

16.00

Depending on Inspection results, if removed, install the

Fasteners at FR44, RH side

6.00

Depending on Inspection results, if necessary, remove

the Fasteners from FR45, LH side

4.00

Depending on Inspection results, remove the Gussets

from FR45, LH side

1.00

Depending on Inspection results, remove the Frame

Foot from FR45, LH side

16.00

Depending on Inspection results, install an identical

Frame Foot at FR45, LH side

16.00

Depending on Inspection results, if removed, install the

Fasteners at FR45, LH side

6.00

Depending on Inspection results, if necessary, remove

the Fasteners from FR45, RH side

4.00

Depending on Inspection results, remove the Gussets

from FR45, RH side

1.00

Depending on Inspection results, remove the Frame

Foot from FR45, RH side

16.00

Depending on Inspection results, install an identical

Frame Foot at FR45, RH side

16.00

Depending on Inspection results, install the Fasteners

at FR45, RH side

6.00

Depending on Inspection results, if necessary, remove

the Fasteners from FR46, LH side

4.00

Depending on Inspection results, remove the Gussets

from FR46, LH side

1.00

Depending on Inspection results, remove the Frame

Foot from FR46, LH side

16.00

Depending on Inspection results, install an identical

Frame Foot at FR46, LH side

16.00

Depending on Inspection results, if removed, install the

Fasteners at FR46, LH side

6.00

Depending on Inspection results, if necessary, remove

the Fasteners from FR46, RH side

4.00

Depending on Inspection results, remove the Gussets

from FR46, RH side

1.00

Depending on Inspection results, remove the Frame

Foot from FR46, RH side

16.00

Depending on Inspection results, install an identical

Frame Foot at FR46, RH side

16.00

Depending on Inspection results, install the Fasteners

at FR46, RH side

6.00

Close-Up 13.00

TOTAL MANHOURS 541.00

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 36

5

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

SERVICE BULLETIN

Task 536177-833-801-001: Repair

ELAPSED TIME (HOURS) 42.00

NOTE: For an explanation of the manhours and elapsed time, refer to the Gantt

Chart, Fig. A-FAAAA given in Appendix 01 - Elapsed Time Assumptions .

NOTE: The minimum manhours necessary to accomplish this Service Bulletin are

those for the Inspection. Depending on the inspection result, additional

manhours can apply.

**CONF 004

Task 536177-839-801-001: Contact and Report to AIRBUS

On Aircraft

Contact and Report to AIRBUS 0.50

TOTAL MANHOURS 0.50

ELAPSED TIME (HOURS) 0.50

**CONF ALL

H. WEIGHT AND BALANCE

Not Changed

I. ELECTRICAL LOAD DATA

Not Changed

J. REFERENCES

**CONF 001

Aircraft Maintenance Manual (AMM) 06-21-00 06-31-53 06-41-00

06-41-53 20-21-12 20-28-11

24-00-00 28-00-00 28-10-00

28-11-00 28-11-29 28-13-21

28-25-00 32-12-11

Consumable Material List (CML)

Drawing R53810322

R53810323

R53810329

R53810330

R53810331

R53810332

Elec. Std. Practices Manual (ESPM) 20-51-20 20-55-00

Service Bulletin (SB) A300-53-6111

A300-53-6176

Standards Manual (SM)

Structural Repair Manual (SRM) 51-24-00 51-40-00 51-40-20

51-40-30 51-40-40

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 37

5

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

SERVICE BULLETIN

**CONF 002

Aircraft Maintenance Manual (AMM) 06-21-00 06-31-53 06-41-00

06-41-53 20-21-12 20-28-11

24-00-00 28-00-00 28-10-00

28-11-00 28-11-29 28-13-21

28-25-00 32-12-11

Consumable Material List (CML)

Elec. Std. Practices Manual (ESPM) 20-51-20 20-55-00

Service Bulletin (SB) A300-53-6111

A300-53-6176

Standards Manual (SM)

Structural Repair Manual (SRM) 51-24-00 51-40-00 51-40-20

51-40-30 51-40-40

**CONF 003

Aircraft Maintenance Manual (AMM) 06-21-00 06-31-53 06-41-00

06-41-53 20-21-12 20-28-11

24-00-00 28-00-00 28-10-00

28-11-00 28-11-29 28-13-21

28-25-00 32-12-11

Consumable Material List (CML)

Drawing R53810322

R53810323

R53810329

R53810330

R53810331

R53810332

Elec. Std. Practices Manual (ESPM) 20-51-20 20-55-00

Service Bulletin (SB) A300-53-6111

A300-53-6176

Standards Manual (SM)

Structural Repair Manual (SRM) 51-24-00 51-40-00 51-40-20

51-40-30 51-40-40

**CONF 004

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

**CONF ALL

K. PUBLICATION AFFECTED

Maintenance Planning Document (MPD) 531541-01-1

L. INTERCHANGEABILITY/MIXABILITY

Not Applicable

M. SPARES

None

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 38

5

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

SERVICE BULLETIN

2. MATERIAL INFORMATION

**CONF ALL

A. MATERIAL - PRICE AND AVAILABILITY

(1) Procurement Addresses

AIRBUS Material, Logistics and Suppliers do not stock standard hardware as competitive

multiple suppliers ensure access to minimum prices. AIRBUS recommends Customers

with aircraft shown in the effectivity of this Service Bulletin to send a purchase order to

KLX Aerospace Solutions. The address is:

Component COMPA01

Component COMPA02

Component COMPA03

Component COMPA04

Component COMPA05

KLX Aerospace Solutions.

10000 NW 15th Terrace Miami

FL 33172

USA

Tel EMEA: +49 (0) 40 822 285 31500

Tel US: +1 305 925 2600

Tel ASIA: +1 310 900 1300

Fax EMEA: +49 (0) 40 822 285 31010

Fax US: +1 305 507 7191

Fax ASIA: +1 310 819 1200

SITA: MIAMMCR

E-Mail: AOGdesk@klx.com

internet: http://www.KLXaerospace.com

or, alternatively any other source on the open

market.

Customers with aircraft shown in the effectivity of this Service Bulletin should send a

purchase order to AIRBUS. Quote the number of this Service Bulletin. The address is:

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 39

5

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

SERVICE BULLETIN

Kit 536177A01R00

Kit 536177A02R00

Kit 536177A03R00

Kit 536177A04R00

Kit 536177A05R00

Kit 536177A06R00

Kit 536177A07R00

Kit 536177A08R00

Kit 536177A09R00

Kit 536177A10R00

Kit 536177A11R00

Kit 536177A12R00

Kit 536177A13R00

Kit 536177A14R00

Kit 536177A15R00

Kit 536177A16R00

Kit 536177A17R00

Kit 536177A18R00

Kit 536177A19R00

Kit 536177A20R00

Kit 536177A21R00

Kit 536177A22R00

Kit 536177A23R00

Kit 536177A24R00

Kit 536177A25R00

Kit 536177A26R00

Kit 536177A27R00

Kit 536177A28R00

Kit 536177A29R00

Kit 536177A30R00

Kit 536177A31R00

Kit 536177A32R00

Kit 536177A33R00

Kit 536177A34R00

Kit 536177A35R00

Kit 536177A36R00

AIRBUS Material, Logistics and Suppliers

Weg beim Jaeger 150

D-22335 HAMBURG

GERMANY

For ordering by internet:

http://spares.airbus.com

For ordering by fax: +49 40 50 76 2590

For ordering by E-mail: airbus.kit@airbus.com

(2) Price and Availability

Kit 536177A01R00

Cost 7,400.00 USD

Availability 180 calendar days from receipt of order

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

order. If items are required before this time, please include a retrofit planning schedule

with your order so that we can try to comply with your requirements. The sales terms

(costs and availability) are estimated in relation to economic conditions. The latest valid

price and lead time for ordering purposes shall be obtained through the AirbusSpares

portal or through a request for quotation to airbus.kit@airbus.com.

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 40

5

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

SERVICE BULLETIN

Kit 536177A02R00

Cost 7,600.00 USD

Availability 180 calendar days from receipt of order

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

order. If items are required before this time, please include a retrofit planning schedule

with your order so that we can try to comply with your requirements. The sales terms

(costs and availability) are estimated in relation to economic conditions. The latest valid

price and lead time for ordering purposes shall be obtained through the AirbusSpares

portal or through a request for quotation to airbus.kit@airbus.com.

Kit 536177A03R00

Cost 8,100.00 USD

Availability 180 calendar days from receipt of order

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

order. If items are required before this time, please include a retrofit planning schedule

with your order so that we can try to comply with your requirements. The sales terms

(costs and availability) are estimated in relation to economic conditions. The latest valid

price and lead time for ordering purposes shall be obtained through the AirbusSpares

portal or through a request for quotation to airbus.kit@airbus.com.

Kit 536177A04R00

Cost 8,100.00 USD

Availability 180 calendar days from receipt of order

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

order. If items are required before this time, please include a retrofit planning schedule

with your order so that we can try to comply with your requirements. The sales terms

(costs and availability) are estimated in relation to economic conditions. The latest valid

price and lead time for ordering purposes shall be obtained through the AirbusSpares

portal or through a request for quotation to airbus.kit@airbus.com.

Kit 536177A05R00

Cost 8,200.00 USD

Availability 180 calendar days from receipt of order

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

order. If items are required before this time, please include a retrofit planning schedule

with your order so that we can try to comply with your requirements. The sales terms

(costs and availability) are estimated in relation to economic conditions. The latest valid

price and lead time for ordering purposes shall be obtained through the AirbusSpares

portal or through a request for quotation to airbus.kit@airbus.com.

Kit 536177A06R00

Cost 8,900.00 USD

Availability 180 calendar days from receipt of order

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 41

5

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

SERVICE BULLETIN

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

order. If items are required before this time, please include a retrofit planning schedule

with your order so that we can try to comply with your requirements. The sales terms

(costs and availability) are estimated in relation to economic conditions. The latest valid

price and lead time for ordering purposes shall be obtained through the AirbusSpares

portal or through a request for quotation to airbus.kit@airbus.com.

Kit 536177A07R00

Cost 7,000.00 USD

Availability 180 calendar days from receipt of order

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

order. If items are required before this time, please include a retrofit planning schedule

with your order so that we can try to comply with your requirements. The sales terms

(costs and availability) are estimated in relation to economic conditions. The latest valid

price and lead time for ordering purposes shall be obtained through the AirbusSpares

portal or through a request for quotation to airbus.kit@airbus.com.

Kit 536177A08R00

Cost 7,100.00 USD

Availability 180 calendar days from receipt of order

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

order. If items are required before this time, please include a retrofit planning schedule

with your order so that we can try to comply with your requirements. The sales terms

(costs and availability) are estimated in relation to economic conditions. The latest valid

price and lead time for ordering purposes shall be obtained through the AirbusSpares

portal or through a request for quotation to airbus.kit@airbus.com.

Kit 536177A09R00

Cost 7,600.00 USD

Availability 180 calendar days from receipt of order

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

order. If items are required before this time, please include a retrofit planning schedule

with your order so that we can try to comply with your requirements. The sales terms

(costs and availability) are estimated in relation to economic conditions. The latest valid

price and lead time for ordering purposes shall be obtained through the AirbusSpares

portal or through a request for quotation to airbus.kit@airbus.com.

Kit 536177A10R00

Cost 6,600.00 USD

Availability 180 calendar days from receipt of order

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

order. If items are required before this time, please include a retrofit planning schedule

with your order so that we can try to comply with your requirements. The sales terms

(costs and availability) are estimated in relation to economic conditions. The latest valid

price and lead time for ordering purposes shall be obtained through the AirbusSpares

portal or through a request for quotation to airbus.kit@airbus.com.

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 42

5

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

SERVICE BULLETIN

Kit 536177A11R00

Cost 6,700.00 USD

Availability 180 calendar days from receipt of order

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

order. If items are required before this time, please include a retrofit planning schedule

with your order so that we can try to comply with your requirements. The sales terms

(costs and availability) are estimated in relation to economic conditions. The latest valid

price and lead time for ordering purposes shall be obtained through the AirbusSpares

portal or through a request for quotation to airbus.kit@airbus.com.

Kit 536177A12R00

Cost 7,300.00 USD

Availability 180 calendar days from receipt of order

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

order. If items are required before this time, please include a retrofit planning schedule

with your order so that we can try to comply with your requirements. The sales terms

(costs and availability) are estimated in relation to economic conditions. The latest valid

price and lead time for ordering purposes shall be obtained through the AirbusSpares

portal or through a request for quotation to airbus.kit@airbus.com.

Kit 536177A13R00

Cost 7,200.00 USD

Availability 180 calendar days from receipt of order

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

order. If items are required before this time, please include a retrofit planning schedule

with your order so that we can try to comply with your requirements. The sales terms

(costs and availability) are estimated in relation to economic conditions. The latest valid

price and lead time for ordering purposes shall be obtained through the AirbusSpares

portal or through a request for quotation to airbus.kit@airbus.com.

Kit 536177A14R00

Cost 7,300.00 USD

Availability 180 calendar days from receipt of order

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

order. If items are required before this time, please include a retrofit planning schedule

with your order so that we can try to comply with your requirements. The sales terms

(costs and availability) are estimated in relation to economic conditions. The latest valid

price and lead time for ordering purposes shall be obtained through the AirbusSpares

portal or through a request for quotation to airbus.kit@airbus.com.

Kit 536177A15R00

Cost 7,900.00 USD

Availability 180 calendar days from receipt of order

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 43

5

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

SERVICE BULLETIN

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

order. If items are required before this time, please include a retrofit planning schedule

with your order so that we can try to comply with your requirements. The sales terms

(costs and availability) are estimated in relation to economic conditions. The latest valid

price and lead time for ordering purposes shall be obtained through the AirbusSpares

portal or through a request for quotation to airbus.kit@airbus.com.

Kit 536177A16R00

Cost 8,200.00 USD

Availability 180 calendar days from receipt of order

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

order. If items are required before this time, please include a retrofit planning schedule

with your order so that we can try to comply with your requirements. The sales terms

(costs and availability) are estimated in relation to economic conditions. The latest valid

price and lead time for ordering purposes shall be obtained through the AirbusSpares

portal or through a request for quotation to airbus.kit@airbus.com.

Kit 536177A17R00

Cost 8,200.00 USD

Availability 180 calendar days from receipt of order

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

order. If items are required before this time, please include a retrofit planning schedule

with your order so that we can try to comply with your requirements. The sales terms

(costs and availability) are estimated in relation to economic conditions. The latest valid

price and lead time for ordering purposes shall be obtained through the AirbusSpares

portal or through a request for quotation to airbus.kit@airbus.com.

Kit 536177A18R00

Cost 8,700.00 USD

Availability 180 calendar days from receipt of order

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

order. If items are required before this time, please include a retrofit planning schedule

with your order so that we can try to comply with your requirements. The sales terms

(costs and availability) are estimated in relation to economic conditions. The latest valid

price and lead time for ordering purposes shall be obtained through the AirbusSpares

portal or through a request for quotation to airbus.kit@airbus.com.

Kit 536177A19R00

Cost 7,400.00 USD

Availability 180 calendar days from receipt of order

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

order. If items are required before this time, please include a retrofit planning schedule

with your order so that we can try to comply with your requirements. The sales terms

(costs and availability) are estimated in relation to economic conditions. The latest valid

price and lead time for ordering purposes shall be obtained through the AirbusSpares

portal or through a request for quotation to airbus.kit@airbus.com.

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 44

5

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

SERVICE BULLETIN

Kit 536177A20R00

Cost 7,600.00 USD

Availability 180 calendar days from receipt of order

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

order. If items are required before this time, please include a retrofit planning schedule

with your order so that we can try to comply with your requirements. The sales terms

(costs and availability) are estimated in relation to economic conditions. The latest valid

price and lead time for ordering purposes shall be obtained through the AirbusSpares

portal or through a request for quotation to airbus.kit@airbus.com.

Kit 536177A21R00

Cost 8,100.00 USD

Availability 180 calendar days from receipt of order

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

order. If items are required before this time, please include a retrofit planning schedule

with your order so that we can try to comply with your requirements. The sales terms

(costs and availability) are estimated in relation to economic conditions. The latest valid

price and lead time for ordering purposes shall be obtained through the AirbusSpares

portal or through a request for quotation to airbus.kit@airbus.com.

Kit 536177A22R00

Cost 8,100.00 USD

Availability 180 calendar days from receipt of order

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

order. If items are required before this time, please include a retrofit planning schedule

with your order so that we can try to comply with your requirements. The sales terms

(costs and availability) are estimated in relation to economic conditions. The latest valid

price and lead time for ordering purposes shall be obtained through the AirbusSpares

portal or through a request for quotation to airbus.kit@airbus.com.

Kit 536177A23R00

Cost 8,200.00 USD

Availability 180 calendar days from receipt of order

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

order. If items are required before this time, please include a retrofit planning schedule

with your order so that we can try to comply with your requirements. The sales terms

(costs and availability) are estimated in relation to economic conditions. The latest valid

price and lead time for ordering purposes shall be obtained through the AirbusSpares

portal or through a request for quotation to airbus.kit@airbus.com.

Kit 536177A24R00

Cost 9,000.00 USD

Availability 180 calendar days from receipt of order

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 45

5

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

SERVICE BULLETIN

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

order. If items are required before this time, please include a retrofit planning schedule

with your order so that we can try to comply with your requirements. The sales terms

(costs and availability) are estimated in relation to economic conditions. The latest valid

price and lead time for ordering purposes shall be obtained through the AirbusSpares

portal or through a request for quotation to airbus.kit@airbus.com.

Kit 536177A25R00

Cost 7,000.00 USD

Availability 180 calendar days from receipt of order

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

order. If items are required before this time, please include a retrofit planning schedule

with your order so that we can try to comply with your requirements. The sales terms

(costs and availability) are estimated in relation to economic conditions. The latest valid

price and lead time for ordering purposes shall be obtained through the AirbusSpares

portal or through a request for quotation to airbus.kit@airbus.com.

Kit 536177A26R00

Cost 7,100.00 USD

Availability 180 calendar days from receipt of order

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

order. If items are required before this time, please include a retrofit planning schedule

with your order so that we can try to comply with your requirements. The sales terms

(costs and availability) are estimated in relation to economic conditions. The latest valid

price and lead time for ordering purposes shall be obtained through the AirbusSpares

portal or through a request for quotation to airbus.kit@airbus.com.

Kit 536177A27R00

Cost 7,600.00 USD

Availability 180 calendar days from receipt of order

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

order. If items are required before this time, please include a retrofit planning schedule

with your order so that we can try to comply with your requirements. The sales terms

(costs and availability) are estimated in relation to economic conditions. The latest valid

price and lead time for ordering purposes shall be obtained through the AirbusSpares

portal or through a request for quotation to airbus.kit@airbus.com.

Kit 536177A28R00

Cost 6,600.00 USD

Availability 180 calendar days from receipt of order

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

order. If items are required before this time, please include a retrofit planning schedule

with your order so that we can try to comply with your requirements. The sales terms

(costs and availability) are estimated in relation to economic conditions. The latest valid

price and lead time for ordering purposes shall be obtained through the AirbusSpares

portal or through a request for quotation to airbus.kit@airbus.com.

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 46

5

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

SERVICE BULLETIN

Kit 536177A29R00

Cost 6,700.00 USD

Availability 180 calendar days from receipt of order

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

order. If items are required before this time, please include a retrofit planning schedule

with your order so that we can try to comply with your requirements. The sales terms

(costs and availability) are estimated in relation to economic conditions. The latest valid

price and lead time for ordering purposes shall be obtained through the AirbusSpares

portal or through a request for quotation to airbus.kit@airbus.com.

Kit 536177A30R00

Cost 7,300.00 USD

Availability 180 calendar days from receipt of order

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

order. If items are required before this time, please include a retrofit planning schedule

with your order so that we can try to comply with your requirements. The sales terms

(costs and availability) are estimated in relation to economic conditions. The latest valid

price and lead time for ordering purposes shall be obtained through the AirbusSpares

portal or through a request for quotation to airbus.kit@airbus.com.

Kit 536177A31R00

Cost 7,200.00 USD

Availability 180 calendar days from receipt of order

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

order. If items are required before this time, please include a retrofit planning schedule

with your order so that we can try to comply with your requirements. The sales terms

(costs and availability) are estimated in relation to economic conditions. The latest valid

price and lead time for ordering purposes shall be obtained through the AirbusSpares

portal or through a request for quotation to airbus.kit@airbus.com.

Kit 536177A32R00

Cost 7,300.00 USD

Availability 180 calendar days from receipt of order

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

order. If items are required before this time, please include a retrofit planning schedule

with your order so that we can try to comply with your requirements. The sales terms

(costs and availability) are estimated in relation to economic conditions. The latest valid

price and lead time for ordering purposes shall be obtained through the AirbusSpares

portal or through a request for quotation to airbus.kit@airbus.com.

Kit 536177A33R00

Cost 7,900.00 USD

Availability 180 calendar days from receipt of order

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 47

5

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

SERVICE BULLETIN

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

order. If items are required before this time, please include a retrofit planning schedule

with your order so that we can try to comply with your requirements. The sales terms

(costs and availability) are estimated in relation to economic conditions. The latest valid

price and lead time for ordering purposes shall be obtained through the AirbusSpares

portal or through a request for quotation to airbus.kit@airbus.com.

Kit 536177A34R00

Cost 8,100.00 USD

Availability 180 calendar days from receipt of order

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

order. If items are required before this time, please include a retrofit planning schedule

with your order so that we can try to comply with your requirements. The sales terms

(costs and availability) are estimated in relation to economic conditions. The latest valid

price and lead time for ordering purposes shall be obtained through the AirbusSpares

portal or through a request for quotation to airbus.kit@airbus.com.

Kit 536177A35R00

Cost 8,200.00 USD

Availability 180 calendar days from receipt of order

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

order. If items are required before this time, please include a retrofit planning schedule

with your order so that we can try to comply with your requirements. The sales terms

(costs and availability) are estimated in relation to economic conditions. The latest valid

price and lead time for ordering purposes shall be obtained through the AirbusSpares

portal or through a request for quotation to airbus.kit@airbus.com.

Kit 536177A36R00

Cost 8,700.00 USD

Availability 180 calendar days from receipt of order

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

order. If items are required before this time, please include a retrofit planning schedule

with your order so that we can try to comply with your requirements. The sales terms

(costs and availability) are estimated in relation to economic conditions. The latest valid

price and lead time for ordering purposes shall be obtained through the AirbusSpares

portal or through a request for quotation to airbus.kit@airbus.com.

Component COMPA01

Operator supplied standard hardware parts required to accomplish this Service Bulletin,

are to be supplied from the operator’s stock.

Component COMPA02

Operator supplied standard hardware parts required to accomplish this Service Bulletin,

are to be supplied from the operator’s stock.

Component COMPA03

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 48

5

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

SERVICE BULLETIN

Operator supplied standard hardware parts required to accomplish this Service Bulletin,

are to be supplied from the operator’s stock.

Component COMPA04

Operator supplied standard hardware parts required to accomplish this Service Bulletin,

are to be supplied from the operator’s stock.

Component COMPA05

Operator supplied standard hardware parts required to accomplish this Service Bulletin,

are to be supplied from the operator’s stock.

B. INDUSTRY SUPPORT INFORMATION

AIRBUS will not provide industry support for accomplishment of this Service Bulletin.

C. LIST OF COMPONENTS

Kit 536177A01R00

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

NOTES

8 EN6115V3A7 15 SCREW

9 ASNA2529-3 36 NUT

10 EN6115V3A6 9 SCREW

12 ASNA2529-6 2 NUT

13 ASNA2001V5-8Y 2 SCREW

14 NAS1726-5E 2 NUT

15 EN6114V5Y8 4 SCREW

16 ASNA2529-5 4 NUT

17 EN6115V3A5 10 SCREW

18 EN6115V3A4 2 SCREW

19 ASNA2050DXJ4020 2 RIVET

21 ASNA2529-4 2 NUT

26 EN6114V6X14 2 SCREW

30 EN6114V4X8 1 SCREW

31 EN6114V4X10 1 SCREW

56 NSA5057-6 4 NUT

100 A5711112920095 1 FOOT

NOTE: If you find part numbers of hardware components in the related kit(s) which

you cannot identify in the LIST OF COMPONENTS of this Service Bulletin,

refer to Standards Manual (SM). The SM will give you the correct part number

to part number relationship.

Kit 536177A02R00

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

NOTES

8 EN6115V3A7 15 SCREW

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 49

5

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

SERVICE BULLETIN

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

NOTES

9 ASNA2529-3 36 NUT

10 EN6115V3A6 9 SCREW

11 EN6114V6Y14 4 SCREW

12 ASNA2529-6 4 NUT

13 ASNA2001V5-8Y 2 SCREW

14 NAS1726-5E 2 NUT

15 EN6114V5Y8 4 SCREW

16 ASNA2529-5 4 NUT

17 EN6115V3A5 10 SCREW

18 EN6115V3A4 2 SCREW

19 ASNA2050DXJ4020 2 RIVET

20 EN6114V4Y9 1 SCREW

21 ASNA2529-4 2 NUT

22 EN6114V4Y10 1 SCREW

56 NSA5057-6 4 NUT

100 A5711112920095 1 FOOT

NOTE: If you find part numbers of hardware components in the related kit(s) which

you cannot identify in the LIST OF COMPONENTS of this Service Bulletin,

refer to Standards Manual (SM). The SM will give you the correct part number

to part number relationship.

Kit 536177A03R00

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

NOTES

9 ASNA2529-3 36 NUT

12 ASNA2529-6 2 NUT

14 NAS1726-5E 2 NUT

16 ASNA2529-5 4 NUT

19 ASNA2050DXJ4020 2 RIVET

21 ASNA2529-4 2 NUT

23 EN6115V3X5 15 SCREW

24 EN6115V3X7 6 SCREW

25 EN6115V3X6 13 SCREW

26 EN6114V6X14 2 SCREW

27 ASNA2001V5-8X 2 SCREW

28 EN6114V5X8 4 SCREW

29 EN6115V3X4 2 SCREW

30 EN6114V4X8 1 SCREW

31 EN6114V4X10 1 SCREW

56 NSA5057-6 4 NUT

100 A5711112920095 1 FOOT

NOTE: If you find part numbers of hardware components in the related kit(s) which

you cannot identify in the LIST OF COMPONENTS of this Service Bulletin,

refer to Standards Manual (SM). The SM will give you the correct part number

to part number relationship.

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 50

5

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@A300-600

SERVICE BULLETIN

Kit 536177A04R00

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

NOTES

8 EN6115V3A7 1 SCREW

9 ASNA2529-3 53 NUT

10 EN6115V3A6 11 SCREW

12 ASNA2529-6 2 NUT

13 ASNA2001V5-8Y 2 SCREW

14 NAS1726-5E 2 NUT

15 EN6114V5Y8 8 SCREW

16 ASNA2529-5 8 NUT

17 EN6115V3A5 10 SCREW

18 EN6115V3A4 4 SCREW

19 ASNA2050DXJ4020 4 RIVET

21 ASNA2529-4 2 NUT

30 EN6114V4X8 1 SCREW

31 EN6114V4X10 1 SCREW

32 EN6115V3A8 14 SCREW

33 EN6115V3A9 11 SCREW

35 EN6114V6X13 2 SCREW

56 NSA5057-6 4 NUT

102 A5711113020095 1 FOOT

NOTE: If you find part numbers of hardware components in the related kit(s) which

you cannot identify in the LIST OF COMPONENTS of this Service Bulletin,

refer to Standards Manual (SM). The SM will give you the correct part number

to part number relationship.

Kit 536177A05R00

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

NOTES

8 EN6115V3A7 1 SCREW

9 ASNA2529-3 53 NUT

10 EN6115V3A6 11 SCREW

12 ASNA2529-6 2 NUT

13 ASNA2001V5-8Y 2 SCREW

14 NAS1726-5E 2 NUT

15 EN6114V5Y8 8 SCREW

16 ASNA2529-5 8 NUT

17 EN6115V3A5 10 SCREW

18 EN6115V3A4 4 SCREW

19 ASNA2050DXJ4020 4 RIVET

20 EN6114V4Y9 1 SCREW

21 ASNA2529-4 2 NUT

22 EN6114V4Y10 1 SCREW

32 EN6115V3A8 14 SCREW

33 EN6115V3A9 11 SCREW

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 51

5

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@A300-600

SERVICE BULLETIN

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

NOTES

34 EN6114V6Y13 2 SCREW

56 NSA5057-6 4 NUT

102 A5711113020095 1 FOOT

NOTE: If you find part numbers of hardware components in the related kit(s) which

you cannot identify in the LIST OF COMPONENTS of this Service Bulletin,

refer to Standards Manual (SM). The SM will give you the correct part number

to part number relationship.

Kit 536177A06R00

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

NOTES

9 ASNA2529-3 48 NUT

12 ASNA2529-6 2 NUT

14 NAS1726-5E 2 NUT

16 ASNA2529-5 8 NUT

19 ASNA2050DXJ4020 4 RIVET

21 ASNA2529-4 2 NUT

23 EN6115V3X5 15 SCREW

24 EN6115V3X7 5 SCREW

25 EN6115V3X6 24 SCREW

27 ASNA2001V5-8X 2 SCREW

28 EN6114V5X8 8 SCREW

29 EN6115V3X4 4 SCREW

30 EN6114V4X8 1 SCREW

31 EN6114V4X10 1 SCREW

35 EN6114V6X13 2 SCREW

56 NSA5057-6 4 NUT

102 A5711113020095 1 FOOT

NOTE: If you find part numbers of hardware components in the related kit(s) which

you cannot identify in the LIST OF COMPONENTS of this Service Bulletin,

refer to Standards Manual (SM). The SM will give you the correct part number

to part number relationship.

Kit 536177A07R00

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

NOTES

8 EN6115V3A7 7 SCREW

9 ASNA2529-3 39 NUT

10 EN6115V3A6 10 SCREW

12 ASNA2529-6 2 NUT

13 ASNA2001V5-8Y 2 SCREW

14 NAS1726-5E 2 NUT

15 EN6114V5Y8 4 SCREW

16 ASNA2529-5 5 NUT

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 52

5

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

SERVICE BULLETIN

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

NOTES

17 EN6115V3A5 9 SCREW

19 ASNA2050DXJ4020 2 RIVET

21 ASNA2529-4 1 NUT

26 EN6114V6X14 2 SCREW

30 EN6114V4X8 1 SCREW

32 EN6115V3A8 11 SCREW

33 EN6115V3A9 1 SCREW

36 EN6115V3A3 5 SCREW

41 EN6114V5X10 1 SCREW

56 NSA5057-6 4 NUT

104 A5711113120095 1 FOOT

NOTE: If you find part numbers of hardware components in the related kit(s) which

you cannot identify in the LIST OF COMPONENTS of this Service Bulletin,

refer to Standards Manual (SM). The SM will give you the correct part number

to part number relationship.

Kit 536177A08R00

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

NOTES

8 EN6115V3A7 7 SCREW

9 ASNA2529-3 39 NUT

10 EN6115V3A6 10 SCREW

11 EN6114V6Y14 2 SCREW

12 ASNA2529-6 2 NUT

13 ASNA2001V5-8Y 2 SCREW

14 NAS1726-5E 2 NUT

15 EN6114V5Y8 4 SCREW

16 ASNA2529-5 5 NUT

17 EN6115V3A5 9 SCREW

19 ASNA2050DXJ4020 2 RIVET

20 EN6114V4Y9 1 SCREW

21 ASNA2529-4 1 NUT

32 EN6115V3A8 11 SCREW

33 EN6115V3A9 1 SCREW

36 EN6115V3A3 5 SCREW

37 EN6114V5Y10 1 SCREW

56 NSA5057-6 4 NUT

104 A5711113120095 1 FOOT

NOTE: If you find part numbers of hardware components in the related kit(s) which

you cannot identify in the LIST OF COMPONENTS of this Service Bulletin,

refer to Standards Manual (SM). The SM will give you the correct part number

to part number relationship.

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 53

5

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@A300-600

SERVICE BULLETIN

Kit 536177A09R00

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

NOTES

9 ASNA2529-3 39 NUT

12 ASNA2529-6 2 NUT

14 NAS1726-5E 2 NUT

16 ASNA2529-5 5 NUT

19 ASNA2050DXJ4020 2 RIVET

21 ASNA2529-4 1 NUT

23 EN6115V3X5 9 SCREW

24 EN6115V3X7 4 SCREW

25 EN6115V3X6 11 SCREW

26 EN6114V6X14 2 SCREW

27 ASNA2001V5-8X 2 SCREW

28 EN6114V5X8 4 SCREW

30 EN6114V4X8 1 SCREW

39 EN6115V3X9 3 SCREW

40 EN6115V3X8 11 SCREW

41 EN6114V5X10 1 SCREW

56 NSA5057-6 4 NUT

104 A5711113120095 1 FOOT

NOTE: If you find part numbers of hardware components in the related kit(s) which

you cannot identify in the LIST OF COMPONENTS of this Service Bulletin,

refer to Standards Manual (SM). The SM will give you the correct part number

to part number relationship.

Kit 536177A10R00

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

NOTES

8 EN6115V3A7 11 SCREW

9 ASNA2529-3 35 NUT

10 EN6115V3A6 12 SCREW

12 ASNA2529-6 2 NUT

13 ASNA2001V5-8Y 2 SCREW

14 NAS1726-5E 2 NUT

15 EN6114V5Y8 2 SCREW

16 ASNA2529-5 4 NUT

17 EN6115V3A5 9 SCREW

18 EN6115V3A4 2 SCREW

19 ASNA2050DXJ4020 2 RIVET

26 EN6114V6X14 2 SCREW

28 EN6114V5X8 1 SCREW

36 EN6115V3A3 1 SCREW

41 EN6114V5X10 1 SCREW

56 NSA5057-6 4 NUT

106 A5711113220095 1 FOOT

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 54

5

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

SERVICE BULLETIN

NOTE: If you find part numbers of hardware components in the related kit(s) which

you cannot identify in the LIST OF COMPONENTS of this Service Bulletin,

refer to Standards Manual (SM). The SM will give you the correct part number

to part number relationship.

Kit 536177A11R00

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

NOTES

8 EN6115V3A7 11 SCREW

9 ASNA2529-3 35 NUT

10 EN6115V3A6 12 SCREW

11 EN6114V6Y14 2 SCREW

12 ASNA2529-6 2 NUT

13 ASNA2001V5-8Y 2 SCREW

14 NAS1726-5E 2 NUT

15 EN6114V5Y8 2 SCREW

16 ASNA2529-5 4 NUT

17 EN6115V3A5 9 SCREW

18 EN6115V3A4 2 SCREW

19 ASNA2050DXJ4020 2 RIVET

36 EN6115V3A3 1 SCREW

37 EN6114V5Y10 2 SCREW

56 NSA5057-6 4 NUT

106 A5711113220095 1 FOOT

NOTE: If you find part numbers of hardware components in the related kit(s) which

you cannot identify in the LIST OF COMPONENTS of this Service Bulletin,

refer to Standards Manual (SM). The SM will give you the correct part number

to part number relationship.

Kit 536177A12R00

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

NOTES

9 ASNA2529-3 35 NUT

12 ASNA2529-6 2 NUT

14 NAS1726-5E 2 NUT

16 ASNA2529-5 4 NUT

19 ASNA2050DXJ4020 2 RIVET

23 EN6115V3X5 10 SCREW

24 EN6115V3X7 11 SCREW

25 EN6115V3X6 12 SCREW

26 EN6114V6X14 2 SCREW

27 ASNA2001V5-8X 2 SCREW

28 EN6114V5X8 3 SCREW

29 EN6115V3X4 2 SCREW

41 EN6114V5X10 1 SCREW

56 NSA5057-6 4 NUT

106 A5711113220095 1 FOOT

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 55

5

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

SERVICE BULLETIN

NOTE: If you find part numbers of hardware components in the related kit(s) which

you cannot identify in the LIST OF COMPONENTS of this Service Bulletin,

refer to Standards Manual (SM). The SM will give you the correct part number

to part number relationship.

Kit 536177A13R00

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

NOTES

8 EN6115V3A7 4 SCREW

9 ASNA2529-3 48 NUT

10 EN6115V3A6 7 SCREW

12 ASNA2529-6 2 NUT

16 ASNA2529-5 2 NUT

17 EN6115V3A5 3 SCREW

19 ASNA2050DXJ4020 4 RIVET

26 EN6114V6X14 2 SCREW

28 EN6114V5X8 1 SCREW

32 EN6115V3A8 7 SCREW

33 EN6115V3A9 17 SCREW

41 EN6114V5X10 1 SCREW

42 EN6114V3A6 1 SCREW

43 EN6115V3A10 2 SCREW

44 EN6115V3A11 7 SCREW

45 ASNA2001V6-8Y 2 SCREW

46 NAS1726-6E 2 NUT

56 NSA5057-6 4 NUT

76 NSA5057-7 4 NUT

108 A5711113320095 1 FOOT

NOTE: If you find part numbers of hardware components in the related kit(s) which

you cannot identify in the LIST OF COMPONENTS of this Service Bulletin,

refer to Standards Manual (SM). The SM will give you the correct part number

to part number relationship.

Kit 536177A14R00

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

NOTES

8 EN6115V3A7 4 SCREW

9 ASNA2529-3 48 NUT

10 EN6115V3A6 7 SCREW

11 EN6114V6Y14 2 SCREW

12 ASNA2529-6 2 NUT

16 ASNA2529-5 2 NUT

17 EN6115V3A5 3 SCREW

19 ASNA2050DXJ4020 4 RIVET

32 EN6115V3A8 7 SCREW

33 EN6115V3A9 17 SCREW

37 EN6114V5Y10 2 SCREW

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 56

5

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

SERVICE BULLETIN

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

NOTES

42 EN6114V3A6 1 SCREW

43 EN6115V3A10 2 SCREW

44 EN6115V3A11 7 SCREW

45 ASNA2001V6-8Y 2 SCREW

46 NAS1726-6E 2 NUT

56 NSA5057-6 4 NUT

76 NSA5057-7 4 NUT

108 A5711113320095 1 FOOT

NOTE: If you find part numbers of hardware components in the related kit(s) which

you cannot identify in the LIST OF COMPONENTS of this Service Bulletin,

refer to Standards Manual (SM). The SM will give you the correct part number

to part number relationship.

Kit 536177A15R00

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

NOTES

9 ASNA2529-3 48 NUT

12 ASNA2529-6 2 NUT

16 ASNA2529-5 2 NUT

19 ASNA2050DXJ4020 4 RIVET

23 EN6115V3X5 8 SCREW

24 EN6115V3X7 7 SCREW

25 EN6115V3X6 18 SCREW

26 EN6114V6X14 2 SCREW

28 EN6114V5X8 1 SCREW

39 EN6115V3X9 4 SCREW

40 EN6115V3X8 10 SCREW

41 EN6114V5X10 1 SCREW

46 NAS1726-6E 2 NUT

47 EN6114V3X6 1 SCREW

48 ASNA2001V6-8X 2 SCREW

56 NSA5057-6 4 NUT

76 NSA5057-7 4 NUT

108 A5711113320095 1 FOOT

NOTE: If you find part numbers of hardware components in the related kit(s) which

you cannot identify in the LIST OF COMPONENTS of this Service Bulletin,

refer to Standards Manual (SM). The SM will give you the correct part number

to part number relationship.

Kit 536177A16R00

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

NOTES

8 EN6115V3A7 3 SCREW

9 ASNA2529-3 43 NUT

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 57

5

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

SERVICE BULLETIN

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

NOTES

10 EN6115V3A6 11 SCREW

12 ASNA2529-6 3 NUT

14 NAS1726-5E 2 NUT

15 EN6114V5Y8 6 SCREW

16 ASNA2529-5 7 NUT

17 EN6115V3A5 7 SCREW

18 EN6115V3A4 2 SCREW

19 ASNA2050DXJ4020 2 RIVET

26 EN6114V6X14 1 SCREW

33 EN6115V3A9 9 SCREW

43 EN6115V3A10 5 SCREW

44 EN6115V3A11 6 SCREW

50 ASNA2001V5-12Y 2 SCREW

52 EN6114V6X17 2 SCREW

54 EN6114V5X12 1 SCREW

56 NSA5057-6 4 NUT

76 NSA5057-7 4 NUT

110 A5711113420095 1 FOOT

NOTE: If you find part numbers of hardware components in the related kit(s) which

you cannot identify in the LIST OF COMPONENTS of this Service Bulletin,

refer to Standards Manual (SM). The SM will give you the correct part number

to part number relationship.

Kit 536177A17R00

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

NOTES

8 EN6115V3A7 3 SCREW

9 ASNA2529-3 43 NUT

10 EN6115V3A6 11 SCREW

11 EN6114V6Y14 1 SCREW

12 ASNA2529-6 3 NUT

14 NAS1726-5E 2 NUT

15 EN6114V5Y8 6 SCREW

16 ASNA2529-5 7 NUT

17 EN6115V3A5 7 SCREW

18 EN6115V3A4 2 SCREW

19 ASNA2050DXJ4020 2 RIVET

33 EN6115V3A9 9 SCREW

43 EN6115V3A10 5 SCREW

44 EN6115V3A11 6 SCREW

49 EN6114V6Y17 2 SCREW

50 ASNA2001V5-12Y 2 SCREW

51 EN6114V5Y12 1 SCREW

56 NSA5057-6 4 NUT

76 NSA5057-7 4 NUT

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 58

5

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

SERVICE BULLETIN

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

NOTES

110 A5711113420095 1 FOOT

NOTE: If you find part numbers of hardware components in the related kit(s) which

you cannot identify in the LIST OF COMPONENTS of this Service Bulletin,

refer to Standards Manual (SM). The SM will give you the correct part number

to part number relationship.

Kit 536177A18R00

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

NOTES

9 ASNA2529-3 43 NUT

12 ASNA2529-6 3 NUT

14 NAS1726-5E 2 NUT

16 ASNA2529-5 7 NUT

19 ASNA2050DXJ4020 2 RIVET

23 EN6115V3X5 12 SCREW

24 EN6115V3X7 10 SCREW

25 EN6115V3X6 19 SCREW

26 EN6114V6X14 1 SCREW

28 EN6114V5X8 6 SCREW

29 EN6115V3X4 2 SCREW

52 EN6114V6X17 2 SCREW

53 ASNA2001V5-12X 2 SCREW

54 EN6114V5X12 1 SCREW

56 NSA5057-6 4 NUT

76 NSA5057-7 4 NUT

110 A5711113420095 1 FOOT

NOTE: If you find part numbers of hardware components in the related kit(s) which

you cannot identify in the LIST OF COMPONENTS of this Service Bulletin,

refer to Standards Manual (SM). The SM will give you the correct part number

to part number relationship.

Kit 536177A19R00

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

NOTES

8 EN6115V3A7 15 SCREW

9 ASNA2529-3 36 NUT

10 EN6115V3A6 9 SCREW

12 ASNA2529-6 2 NUT

13 ASNA2001V5-8Y 2 SCREW

14 NAS1726-5E 2 NUT

15 EN6114V5Y8 4 SCREW

16 ASNA2529-5 4 NUT

17 EN6115V3A5 10 SCREW

18 EN6115V3A4 2 SCREW

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 59

5

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

SERVICE BULLETIN

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

NOTES

19 ASNA2050DXJ4020 2 RIVET

21 ASNA2529-4 2 NUT

26 EN6114V6X14 2 SCREW

30 EN6114V4X8 1 SCREW

31 EN6114V4X10 1 SCREW

56 NSA5057-6 4 NUT

101 A5711112920195 1 FOOT

NOTE: If you find part numbers of hardware components in the related kit(s) which

you cannot identify in the LIST OF COMPONENTS of this Service Bulletin,

refer to Standards Manual (SM). The SM will give you the correct part number

to part number relationship.

Kit 536177A20R00

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

NOTES

8 EN6115V3A7 15 SCREW

9 ASNA2529-3 36 NUT

10 EN6115V3A6 9 SCREW

11 EN6114V6Y14 4 SCREW

12 ASNA2529-6 4 NUT

13 ASNA2001V5-8Y 2 SCREW

14 NAS1726-5E 2 NUT

15 EN6114V5Y8 4 SCREW

16 ASNA2529-5 4 NUT

17 EN6115V3A5 10 SCREW

18 EN6115V3A4 2 SCREW

19 ASNA2050DXJ4020 2 RIVET

20 EN6114V4Y9 1 SCREW

21 ASNA2529-4 2 NUT

22 EN6114V4Y10 1 SCREW

56 NSA5057-6 4 NUT

101 A5711112920195 1 FOOT

NOTE: If you find part numbers of hardware components in the related kit(s) which

you cannot identify in the LIST OF COMPONENTS of this Service Bulletin,

refer to Standards Manual (SM). The SM will give you the correct part number

to part number relationship.

Kit 536177A21R00

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

NOTES

9 ASNA2529-3 36 NUT

12 ASNA2529-6 2 NUT

14 NAS1726-5E 2 NUT

16 ASNA2529-5 4 NUT

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 60

5

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@A300-600

SERVICE BULLETIN

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

NOTES

19 ASNA2050DXJ4020 2 RIVET

21 ASNA2529-4 2 NUT

23 EN6115V3X5 15 SCREW

24 EN6115V3X7 6 SCREW

25 EN6115V3X6 13 SCREW

26 EN6114V6X14 2 SCREW

27 ASNA2001V5-8X 2 SCREW

28 EN6114V5X8 4 SCREW

29 EN6115V3X4 2 SCREW

30 EN6114V4X8 1 SCREW

31 EN6114V4X10 1 SCREW

56 NSA5057-6 4 NUT

101 A5711112920195 1 FOOT

NOTE: If you find part numbers of hardware components in the related kit(s) which

you cannot identify in the LIST OF COMPONENTS of this Service Bulletin,

refer to Standards Manual (SM). The SM will give you the correct part number

to part number relationship.

Kit 536177A22R00

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

NOTES

8 EN6115V3A7 1 SCREW

9 ASNA2529-3 53 NUT

10 EN6115V3A6 11 SCREW

12 ASNA2529-6 2 NUT

13 ASNA2001V5-8Y 2 SCREW

14 NAS1726-5E 2 NUT

15 EN6114V5Y8 8 SCREW

16 ASNA2529-5 8 NUT

17 EN6115V3A5 10 SCREW

18 EN6115V3A4 4 SCREW

19 ASNA2050DXJ4020 4 RIVET

21 ASNA2529-4 2 NUT

30 EN6114V4X8 1 SCREW

31 EN6114V4X10 1 SCREW

32 EN6115V3A8 14 SCREW

33 EN6115V3A9 11 SCREW

35 EN6114V6X13 2 SCREW

56 NSA5057-6 4 NUT

103 A5711113020195 1 FOOT

NOTE: If you find part numbers of hardware components in the related kit(s) which

you cannot identify in the LIST OF COMPONENTS of this Service Bulletin,

refer to Standards Manual (SM). The SM will give you the correct part number

to part number relationship.

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 61

5

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

SERVICE BULLETIN

Kit 536177A23R00

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

NOTES

8 EN6115V3A7 1 SCREW

9 ASNA2529-3 53 NUT

10 EN6115V3A6 11 SCREW

12 ASNA2529-6 2 NUT

13 ASNA2001V5-8Y 2 SCREW

14 NAS1726-5E 2 NUT

15 EN6114V5Y8 8 SCREW

16 ASNA2529-5 8 NUT

17 EN6115V3A5 10 SCREW

18 EN6115V3A4 4 SCREW

19 ASNA2050DXJ4020 4 RIVET

20 EN6114V4Y9 1 SCREW

21 ASNA2529-4 2 NUT

22 EN6114V4Y10 1 SCREW

32 EN6115V3A8 14 SCREW

33 EN6115V3A9 11 SCREW

34 EN6114V6Y13 2 SCREW

56 NSA5057-6 4 NUT

103 A5711113020195 1 FOOT

NOTE: If you find part numbers of hardware components in the related kit(s) which

you cannot identify in the LIST OF COMPONENTS of this Service Bulletin,

refer to Standards Manual (SM). The SM will give you the correct part number

to part number relationship.

Kit 536177A24R00

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

NOTES

9 ASNA2529-3 48 NUT

12 ASNA2529-6 2 NUT

14 NAS1726-5E 2 NUT

16 ASNA2529-5 8 NUT

19 ASNA2050DXJ4020 4 RIVET

21 ASNA2529-4 2 NUT

23 EN6115V3X15 5 SCREW

23 EN6115V3X5 10 SCREW

24 EN6115V3X7 5 SCREW

25 EN6115V3X6 24 SCREW

27 ASNA2001V5-8X 2 SCREW

28 EN6114V5X8 8 SCREW

29 EN6115V3X4 4 SCREW

30 EN6114V4X8 1 SCREW

31 EN6114V4X10 1 SCREW

35 EN6114V6X13 2 SCREW

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 62

5

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@A300-600

SERVICE BULLETIN

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

NOTES

56 NSA5057-6 4 NUT

103 A5711113020195 1 FOOT

NOTE: If you find part numbers of hardware components in the related kit(s) which

you cannot identify in the LIST OF COMPONENTS of this Service Bulletin,

refer to Standards Manual (SM). The SM will give you the correct part number

to part number relationship.

Kit 536177A25R00

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

NOTES

8 EN6115V3A7 7 SCREW

9 ASNA2529-3 39 NUT

10 EN6115V3A6 10 SCREW

12 ASNA2529-6 2 NUT

13 ASNA2001V5-8Y 2 SCREW

14 NAS1726-5E 2 NUT

15 EN6114V5Y8 4 SCREW

16 ASNA2529-5 5 NUT

17 EN6115V3A5 9 SCREW

19 ASNA2050DXJ4020 2 RIVET

21 ASNA2529-4 1 NUT

26 EN6114V6X14 2 SCREW

30 EN6114V4X8 1 SCREW

32 EN6115V3A8 11 SCREW

33 EN6115V3A9 1 SCREW

36 EN6115V3A3 5 SCREW

41 EN6114V5X10 1 SCREW

56 NSA5057-6 4 NUT

105 A5711113120195 1 FOOT

NOTE: If you find part numbers of hardware components in the related kit(s) which

you cannot identify in the LIST OF COMPONENTS of this Service Bulletin,

refer to Standards Manual (SM). The SM will give you the correct part number

to part number relationship.

Kit 536177A26R00

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

NOTES

8 EN6115V3A7 7 SCREW

9 ASNA2529-3 39 NUT

10 EN6115V3A6 10 SCREW

11 EN6114V6Y14 2 SCREW

12 ASNA2529-6 2 NUT

13 ASNA2001V5-8Y 2 SCREW

14 NAS1726-5E 2 NUT

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 63

5

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@A300-600

SERVICE BULLETIN

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

NOTES

15 EN6114V5Y8 4 SCREW

16 ASNA2529-5 5 NUT

17 EN6115V3A5 9 SCREW

19 ASNA2050DXJ4020 2 RIVET

20 EN6114V4Y9 1 SCREW

21 ASNA2529-4 1 NUT

32 EN6115V3A8 11 SCREW

33 EN6115V3A9 1 SCREW

36 EN6115V3A3 5 SCREW

37 EN6114V5Y10 1 SCREW

56 NSA5057-6 4 NUT

105 A5711113120195 1 FOOT

NOTE: If you find part numbers of hardware components in the related kit(s) which

you cannot identify in the LIST OF COMPONENTS of this Service Bulletin,

refer to Standards Manual (SM). The SM will give you the correct part number

to part number relationship.

Kit 536177A27R00

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

NOTES

9 ASNA2529-3 39 NUT

12 ASNA2529-6 2 NUT

14 NAS1726-5E 2 NUT

16 ASNA2529-5 5 NUT

19 ASNA2050DXJ4020 2 RIVET

21 ASNA2529-4 1 NUT

23 EN6115V3X5 9 SCREW

24 EN6115V3X7 4 SCREW

25 EN6115V3X6 11 SCREW

26 EN6114V6X14 2 SCREW

27 ASNA2001V5-8X 2 SCREW

28 EN6114V5X8 4 SCREW

30 EN6114V4X8 1 SCREW

39 EN6115V3X9 3 SCREW

40 EN6115V3X8 11 SCREW

41 EN6114V5X10 1 SCREW

56 NSA5057-6 4 NUT

105 A5711113120195 1 FOOT

NOTE: If you find part numbers of hardware components in the related kit(s) which

you cannot identify in the LIST OF COMPONENTS of this Service Bulletin,

refer to Standards Manual (SM). The SM will give you the correct part number

to part number relationship.

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 64

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@A300-600

SERVICE BULLETIN

Kit 536177A28R00

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

NOTES

8 EN6115V3A7 11 SCREW

9 ASNA2529-3 35 NUT

10 EN6115V3A6 12 SCREW

12 ASNA2529-6 2 NUT

13 ASNA2001V5-8Y 2 SCREW

14 NAS1726-5E 2 NUT

15 EN6114V5Y8 2 SCREW

16 ASNA2529-5 4 NUT

17 EN6115V3A5 9 SCREW

18 EN6115V3A4 2 SCREW

19 ASNA2050DXJ4020 2 RIVET

26 EN6114V6X14 2 SCREW

28 EN6114V5X8 1 SCREW

36 EN6115V3A3 1 SCREW

41 EN6114V5X10 1 SCREW

56 NSA5057-6 4 NUT

107 A5711113220195 1 FOOT

NOTE: If you find part numbers of hardware components in the related kit(s) which

you cannot identify in the LIST OF COMPONENTS of this Service Bulletin,

refer to Standards Manual (SM). The SM will give you the correct part number

to part number relationship.

Kit 536177A29R00

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

NOTES

8 EN6115V3A7 11 SCREW

9 ASNA2529-3 35 NUT

10 EN6115V3A6 12 SCREW

11 EN6114V6Y14 2 SCREW

12 ASNA2529-6 2 NUT

13 ASNA2001V5-8Y 2 SCREW

14 NAS1726-5E 2 NUT

15 EN6114V5Y8 2 SCREW

16 ASNA2529-5 4 NUT

17 EN6115V3A5 9 SCREW

18 EN6115V3A4 2 SCREW

19 ASNA2050DXJ4020 2 RIVET

36 EN6115V3A3 1 SCREW

37 EN6114V5Y10 2 SCREW

56 NSA5057-6 4 NUT

107 A5711113220195 1 FOOT

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 65

5

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

SERVICE BULLETIN

NOTE: If you find part numbers of hardware components in the related kit(s) which

you cannot identify in the LIST OF COMPONENTS of this Service Bulletin,

refer to Standards Manual (SM). The SM will give you the correct part number

to part number relationship.

Kit 536177A30R00

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

NOTES

9 ASNA2529-3 35 NUT

12 ASNA2529-6 2 NUT

14 NAS1726-5E 2 NUT

16 ASNA2529-5 4 NUT

19 ASNA2050DXJ4020 2 RIVET

23 EN6115V3X5 10 SCREW

24 EN6115V3X7 11 SCREW

25 EN6115V3X6 12 SCREW

26 EN6114V6X14 2 SCREW

27 ASNA2001V5-8X 2 SCREW

28 EN6114V5X8 3 SCREW

29 EN6115V3X4 2 SCREW

41 EN6114V5X10 1 SCREW

56 NSA5057-6 4 NUT

107 A5711113220195 1 FOOT

NOTE: If you find part numbers of hardware components in the related kit(s) which

you cannot identify in the LIST OF COMPONENTS of this Service Bulletin,

refer to Standards Manual (SM). The SM will give you the correct part number

to part number relationship.

Kit 536177A31R00

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

NOTES

8 EN6115V3A7 4 SCREW

9 ASNA2529-3 48 NUT

10 EN6115V3A6 5 SCREW

12 ASNA2529-6 2 NUT

16 ASNA2529-5 2 NUT

17 EN6115V3A5 5 SCREW

19 ASNA2050DXJ4020 4 RIVET

26 EN6114V6X14 2 SCREW

28 EN6114V5X8 1 SCREW

32 EN6115V3A8 7 SCREW

33 EN6115V3A9 17 SCREW

41 EN6114V5X10 1 SCREW

42 EN6114V3A6 1 SCREW

43 EN6115V3A10 2 SCREW

44 EN6115V3A11 7 SCREW

45 ASNA2001V6-8Y 2 SCREW

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 66

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@A300-600

SERVICE BULLETIN

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

NOTES

46 NAS1726-6E 2 NUT

56 NSA5057-6 4 NUT

76 NSA5057-7 4 NUT

109 A5711113320195 1 FOOT

NOTE: If you find part numbers of hardware components in the related kit(s) which

you cannot identify in the LIST OF COMPONENTS of this Service Bulletin,

refer to Standards Manual (SM). The SM will give you the correct part number

to part number relationship.

Kit 536177A32R00

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

NOTES

8 EN6115V3A7 4 SCREW

9 ASNA2529-3 48 NUT

10 EN6115V3A6 5 SCREW

11 EN6114V6Y14 2 SCREW

12 ASNA2529-6 2 NUT

16 ASNA2529-5 2 NUT

17 EN6115V3A5 5 SCREW

19 ASNA2050DXJ4020 4 RIVET

32 EN6115V3A8 7 SCREW

33 EN6115V3A9 17 SCREW

37 EN6114V5Y10 2 SCREW

42 EN6114V3A6 1 SCREW

43 EN6115V3A10 2 SCREW

44 EN6115V3A11 7 SCREW

45 ASNA2001V6-8Y 2 SCREW

46 NAS1726-6E 2 NUT

56 NSA5057-6 4 NUT

76 NSA5057-7 4 NUT

109 A5711113320195 1 FOOT

NOTE: If you find part numbers of hardware components in the related kit(s) which

you cannot identify in the LIST OF COMPONENTS of this Service Bulletin,

refer to Standards Manual (SM). The SM will give you the correct part number

to part number relationship.

Kit 536177A33R00

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

NOTES

9 ASNA2529-3 48 NUT

12 ASNA2529-6 2 NUT

16 ASNA2529-5 2 NUT

19 ASNA2050DXJ4020 4 RIVET

23 EN6115V3X5 10 SCREW

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 67

5

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@A300-600

SERVICE BULLETIN

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

NOTES

24 EN6115V3X7 7 SCREW

25 EN6115V3X6 16 SCREW

26 EN6114V6X14 2 SCREW

28 EN6114V5X8 1 SCREW

39 EN6115V3X9 4 SCREW

40 EN6115V3X8 10 SCREW

41 EN6114V5X10 1 SCREW

46 NAS1726-6E 2 NUT

47 EN6114V3X6 1 SCREW

48 ASNA2001V6-8X 2 SCREW

56 NSA5057-6 4 NUT

76 NSA5057-7 4 NUT

109 A5711113320195 1 FOOT

NOTE: If you find part numbers of hardware components in the related kit(s) which

you cannot identify in the LIST OF COMPONENTS of this Service Bulletin,

refer to Standards Manual (SM). The SM will give you the correct part number

to part number relationship.

Kit 536177A34R00

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

NOTES

8 EN6115V3A7 3 SCREW

9 ASNA2529-3 43 NUT

10 EN6115V3A6 8 SCREW

12 ASNA2529-6 3 NUT

14 NAS1726-5E 2 NUT

15 EN6114V5Y8 6 SCREW

16 ASNA2529-5 7 NUT

17 EN6115V3A5 7 SCREW

18 EN6115V3A4 2 SCREW

19 ASNA2050DXJ4020 2 RIVET

26 EN6114V6X14 1 SCREW

33 EN6115V3A9 9 SCREW

43 EN6115V3A10 5 SCREW

44 EN6115V3A11 6 SCREW

50 ASNA2001V5-12Y 2 SCREW

52 EN6114V6X17 2 SCREW

54 EN6114V5X12 1 SCREW

56 NSA5057-6 4 NUT

76 NSA5057-7 4 NUT

111 A5711113420195 1 FOOT

NOTE: If you find part numbers of hardware components in the related kit(s) which

you cannot identify in the LIST OF COMPONENTS of this Service Bulletin,

refer to Standards Manual (SM). The SM will give you the correct part number

to part number relationship.

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 68

5

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@A300-600

SERVICE BULLETIN

Kit 536177A35R00

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

NOTES

8 EN6115V3A7 3 SCREW

9 ASNA2529-3 43 NUT

10 EN6115V3A6 8 SCREW

11 EN6114V6Y14 1 SCREW

12 ASNA2529-6 3 NUT

14 NAS1726-5E 2 NUT

15 EN6114V5Y8 6 SCREW

16 ASNA2529-5 7 NUT

17 EN6115V3A5 7 SCREW

18 EN6115V3A4 2 SCREW

19 ASNA2050DXJ4020 2 RIVET

33 EN6115V3A9 9 SCREW

43 EN6115V3A10 5 SCREW

44 EN6115V3A11 6 SCREW

49 EN6114V6Y17 2 SCREW

50 ASNA2001V5-12Y 2 SCREW

51 EN6114V5Y12 1 SCREW

56 NSA5057-6 4 NUT

76 NSA5057-7 4 NUT

111 A5711113420195 1 FOOT

NOTE: If you find part numbers of hardware components in the related kit(s) which

you cannot identify in the LIST OF COMPONENTS of this Service Bulletin,

refer to Standards Manual (SM). The SM will give you the correct part number

to part number relationship.

Kit 536177A36R00

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

NOTES

9 ASNA2529-3 43 NUT

12 ASNA2529-6 3 NUT

14 NAS1726-5E 2 NUT

16 ASNA2529-5 7 NUT

19 ASNA2050DXJ4020 2 RIVET

23 EN6115V3X5 12 SCREW

24 EN6115V3X7 10 SCREW

25 EN6115V3X6 19 SCREW

26 EN6114V6X14 1 SCREW

28 EN6114V5X8 6 SCREW

29 EN6115V3X4 2 SCREW

52 EN6114V6X17 2 SCREW

53 ASNA2001V5-12X 2 SCREW

54 EN6114V5X12 1 SCREW

56 NSA5057-6 4 NUT

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 69

5

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@A300-600

SERVICE BULLETIN

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

NOTES

76 NSA5057-7 4 NUT

111 A5711113420195 1 FOOT

NOTE: If you find part numbers of hardware components in the related kit(s) which

you cannot identify in the LIST OF COMPONENTS of this Service Bulletin,

refer to Standards Manual (SM). The SM will give you the correct part number

to part number relationship.

D. LIST OF MATERIALS - OPERATOR SUPPLIED

(1) Consumable Materials

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO CML

MAT. No.

QTY PER A/C SEE

NOTES

Wash Primer - Structure 04CMA2 As required

Primer Polyurethane Paint -

Corrosion Inhibiting

04EAC2 As required

Polysulfide Sealant - General

Purpose Brushable

06AAA1 As required

Polysulfide Sealant - Fuel Tank

Brushable

06ABA1 As required

Polysulfide Sealant - Fuel Tank

Fillet

06ABB1 As required

Non Aqueous Cleaner - General 08BAA9 As required

(2) Components

Component COMPA01

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

NOTES

9 ASNA2529-3 32 NUT

90 ASNA2019-56-25 32 RIVET

91 EN6114V3X5 32 SCREW

92 EN6080D6X-32 20 RIVET

NOTE: If you find part numbers of hardware components in the related kit(s)

which you cannot identify in the LIST OF COMPONENTS of this Service

Bulletin, refer to Standards Manual (SM). The SM will give you the

correct part number to part number relationship.

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

NOTE: The components listed above are only necessary if crack is found on a

Frame foot. The quantity of these items are to be ordered as required.

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 70

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@A300-600

SERVICE BULLETIN

Component COMPA02

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

NOTES

9 ASNA2529-3 24 NUT

90 ASNA2019-56-25 24 RIVET

91 EN6114V3X5 24 SCREW

92 EN6080D6X-32 16 RIVET

NOTE: If you find part numbers of hardware components in the related kit(s)

which you cannot identify in the LIST OF COMPONENTS of this Service

Bulletin, refer to Standards Manual (SM). The SM will give you the

correct part number to part number relationship.

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

NOTE: The components listed above are only necessary if crack is found on a

Frame foot. The quantity of these items are to be ordered as required.

Component COMPA03

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

NOTES

9 ASNA2529-3 24 NUT

47 EN6114V3X6 24 SCREW

90 ASNA2019-56-25 24 RIVET

92 EN6080D6X-32 16 RIVET

NOTE: If you find part numbers of hardware components in the related kit(s)

which you cannot identify in the LIST OF COMPONENTS of this Service

Bulletin, refer to Standards Manual (SM). The SM will give you the

correct part number to part number relationship.

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

NOTE: The components listed above are only necessary if crack is found on a

Frame foot. The quantity of these items are to be ordered as required.

Component COMPA04

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

NOTES

9 ASNA2529-3 32 NUT

47 EN6114V3X6 32 SCREW

90 ASNA2019-56-25 32 RIVET

92 EN6080D6X-32 20 RIVET

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 71

5

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

SERVICE BULLETIN

NOTE: If you find part numbers of hardware components in the related kit(s)

which you cannot identify in the LIST OF COMPONENTS of this Service

Bulletin, refer to Standards Manual (SM). The SM will give you the

correct part number to part number relationship.

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

NOTE: The components listed above are only necessary if crack is found on a

Frame foot. The quantity of these items are to be ordered as required.

Component COMPA05

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

NOTES

9 ASNA2529-3 24 NUT

47 EN6114V3X6 16 SCREW

90 ASNA2019-56-25 24 RIVET

91 EN6114V3X5 8 SCREW

92 EN6080D6X-32 16 RIVET

NOTE: If you find part numbers of hardware components in the related kit(s)

which you cannot identify in the LIST OF COMPONENTS of this Service

Bulletin, refer to Standards Manual (SM). The SM will give you the

correct part number to part number relationship.

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

NOTE: The components listed above are only necessary if crack is found on a

Frame foot. The quantity of these items are to be ordered as required.

(3) Equipment

None

E. PARTS TO BE RE-IDENTIFIED BY OPERATOR

None

F. TOOLING

None

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 72

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@A300-600

SERVICE BULLETIN

3. ACCOMPLISHMENT INSTRUCTIONS

Task 536177-832-801-001 - Detailed Inspection of the Frame foot

WARNING: MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS

INCLUDED IN THE REFERENCED PROCEDURES.

CAUTION: ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP

ELECTRICAL WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY

AND MECHANICALLY SERVICEABLE). WHEN YOU DO MAINTENANCE

WORK, REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING,

COMPONENTS AND THE WORK AREA AS CLEAN AS POSSIBLE. TO DO

THIS:

- PUT PROTECTION, SUCH AS PLASTIC SHEETING, CLOTHS, ETC, AS

NECESSARY ON WIRING AND COMPONENTS.

- REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND

OTHER CONTAMINATION.

THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION

AND DAMAGE TO THE ELECTRICAL WIRING INSTALLATION.

IF THERE IS CONTAMINATION, REFER TO ESPM 20-55-00.

NOTE: The accomplishment instructions of this Service Bulletin include procedures given

in other documents or in other sections of the Service Bulletin. When the words

"refer to" are used and the operator has a procedure accepted by the local

authority he belongs to, the accepted alternative procedure can be used. When the

words "in accordance with" are used then the given procedure must be followed.

NOTE: The access and close-up instructions, not comprising return to service tests, in this

Service Bulletin do not constitute or affect the technical intent of the Service

Bulletin. Operators can therefore, as deemed necessary, omit or add access and/or

close-up steps to add flexibility to their maintenance operations as long as the

technical intent of the Service Bulletin is met within the set parameters.

NOTE: Manual titles given in the accomplishment instructions are referred to by acronyms.

Refer to paragraph 1.J., References, for the definition of acronyms.

NOTE: The purpose of flow charts is to supplement the information given in the Procedure

and Compliance paragraphs and not to serve as the primary source for tasks or

compliance times given in this Service Bulletin.

NOTE: This Service Bulletin is classified mandatory or expected to be classified mandatory

by an Airworthiness Directive (AD). The paragraphs 3.C. and 3.D. in these

accomplishment instructions are Required for Compliance (RC) and must be done

to comply with the AD. Other paragraphs are recommended and may be deviated

from, done as part of other actions or done with accepted methods different from

those given in the Service Bulletin, as long as the RC paragraphs can be done and

the aircraft can be put back into a serviceable condition.

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 73

5

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

SERVICE BULLETIN

Task Associated Data

**CONF 001

Zone

147 148

Access

Door 147BZ

Manpower

TOTAL MANHOURS 8.00

ELAPSED TIME (HOURS) 2.50

**CONF 002

Zone

147 148

Access

Door 147AZ 147BZ

Manpower

TOTAL MANHOURS 8.00

ELAPSED TIME (HOURS) 2.50

**CONF 003

Zone

147 148

Access

Door 147BZ

Manpower

TOTAL MANHOURS 8.00

ELAPSED TIME (HOURS) 2.50

**CONF 004

None

**CONF ALL

A. GENERAL

**CONF 001

(1) Subtask 536177-910-001-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 74

5

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

SERVICE BULLETIN

References

Aircraft Maintenance Manual (AMM) 06-21-00, Page Block 001

06-31-53, Page Block 001

06-41-00, Page Block 001

Consumable Material List (CML)

(a) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001.

(b) For the identification of zones, refer to AMM 06-21-00, Page Block 001.

(c) For the identification of access panels, refer to AMM 06-41-00, Page Block 001.

(d) For the specification of materials (Mat. No.) given in this Service Bulletin, refer to

the Consumable Material List (CML).

(2) Subtask 536177-839-001-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

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

Service Bulletin.

**CONF 002

(1) Subtask 536177-910-001-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-21-00, Page Block 001

06-31-53, Page Block 001

06-41-00, Page Block 001

Consumable Material List (CML)

(a) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001.

(b) For the identification of zones, refer to AMM 06-21-00, Page Block 001.

(c) For the identification of access panels, refer to AMM 06-41-00, Page Block 001.

(d) For the specification of materials (Mat. No.) given in this Service Bulletin, refer to

the Consumable Material List (CML).

(2) Subtask 536177-839-001-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

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

Service Bulletin.

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 75

5

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

SERVICE BULLETIN

**CONF 003

(1) Subtask 536177-910-001-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-21-00, Page Block 001

06-31-53, Page Block 001

06-41-00, Page Block 001

Consumable Material List (CML)

(a) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001.

(b) For the identification of zones, refer to AMM 06-21-00, Page Block 001.

(c) For the identification of access panels, refer to AMM 06-41-00, Page Block 001.

(d) For the specification of materials (Mat. No.) given in this Service Bulletin, refer to

the Consumable Material List (CML).

(2) Subtask 536177-839-001-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

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

Service Bulletin.

**CONF 004

None

**CONF ALL

B. PREPARATION

**CONF 001

(1) Subtask 536177-941-001-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-41-53, Page Block 001

24-00-00, Page Block 301

32-12-11, Page Block 301

NOTE: The items given in this note shall be considered as the basic Aircraft

configuration before you start a maintenance task:

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 76

5

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

SERVICE BULLETIN

- Aircraft on the ground resting on landing gear (the ground safety

locks and the wheel chocks are in position on the landing gear)

- Engine shut down, thrust reversers closed and locked

- Aircraft in clean configuration

- Parking brake applied

- Aircraft electrical network de-energized

- Hydraulic systems depressurized

- Access to the cockpit and cabin is available

- All circuit breakers are in closed position

- All controls in NORM, AUTO or OFF position

(a) Make sure that the aircraft is electrically grounded, refer to AMM 24-00-00, Page

Block 301.

(b) Open the Main Landing Gear (MLG) door, refer to AMM 32-12-11, Page Block 301.

(c) Put an access platform in position at zone 140.

(d) Open the access door 147BZ, refer to AMM 06-41-53, Page Block 001.

**CONF 002

(1) Subtask 536177-941-001-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-41-53, Page Block 001

24-00-00, Page Block 301

32-12-11, Page Block 301

NOTE: The items given in this note shall be considered as the basic Aircraft

configuration before you start a maintenance task:

- Aircraft on the ground resting on landing gear (the ground safety

locks and the wheel chocks are in position on the landing gear)

- Engine shut down, thrust reversers closed and locked

- Aircraft in clean configuration

- Parking brake applied

- Aircraft electrical network de-energized

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 77

5

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

SERVICE BULLETIN

- Hydraulic systems depressurized

- Access to the cockpit and cabin is available

- All circuit breakers are in closed position

- All controls in NORM, AUTO or OFF position

(a) Make sure that the aircraft is electrically grounded, refer to AMM 24-00-00, Page

Block 301.

(b) Open the Main Landing Gear (MLG) door, refer to AMM 32-12-11, Page Block 301.

(c) Put an access platform in position at zone 140.

(d) Open the access door 147BZ, refer to AMM 06-41-53, Page Block 001.

**CONF 003

(1) Subtask 536177-941-001-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-41-53, Page Block 001

24-00-00, Page Block 301

32-12-11, Page Block 301

NOTE: The items given in this note shall be considered as the basic Aircraft

configuration before you start a maintenance task:

- Aircraft on the ground resting on landing gear (the ground safety

locks and the wheel chocks are in position on the landing gear)

- Engine shut down, thrust reversers closed and locked

- Aircraft in clean configuration

- Parking brake applied

- Aircraft electrical network de-energized

- Hydraulic systems depressurized

- Access to the cockpit and cabin is available

- All circuit breakers are in closed position

- All controls in NORM, AUTO or OFF position

(a) Make sure that the aircraft is electrically grounded, refer to AMM 24-00-00, Page

Block 301.

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 78

5

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

SERVICE BULLETIN

(b) Open the Main Landing Gear (MLG) door, refer to AMM 32-12-11, Page Block 301.

(c) Put an access platform in position at zone 140.

(d) Open the access door 147BZ, refer to AMM 06-41-53, Page Block 001.

**CONF 004

None

**CONF ALL

C. PROCEDURE

**CONF 001

(1) Subtask 536177-832-001-001 - Do a Detailed Inspection of the Frame Foot at FR41

on LH Side

Work Zones and Access Panels

Zone Access/Work location

147 Access Door 147BZ

Work location Frame 41

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Non Aqueous Cleaner -

General

08BAA9 As required

References

Drawing R53810329

Service Bulletin (SB) A300-53-6111

A300-53-6176

Fig. A-FFAAA

Flow Chart for Frame 41 on LH side

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Fig. A-FRAAA

Inspection report

Sheet 01

Sheet 02

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 79

5

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

SERVICE BULLETIN

References

Fig. A-FBAAA

Inspection areas

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

(a) At threshold given in the PLANNING INFORMATION Paragraph E.(2):

Do a detailed inspection of the Frame foot at Frame 41 on LH side.

Refer to Fig. A-FFAAA

Refer to Fig. A-FBAAA Sheet 01, Fig. A-FBAAA Sheet 02 and Fig. A-FBAAA Sheet

08

1 The Frame have never been inspected as per Service Bulletin No.

A300-53-6111 or never be repaired as per Service Bulletin No. A300-53-6111

or never be repaired as per R53810329:

a Clean the inspected areas with:

Non Aqueous

Cleaner - General

08BAA9 As required

b Do a detailed inspection of the area 1 and the area 2 of Frame foot at

Frame 41 on LH side.

<1> If crack is not found in area 1 or area 2:

<a> Repeat the inspection of the Frame foot at Frame 41 on LH

side, at the interval given in the table 2 of the planning

information paragraph E.(2).

OR

<b> Apply Service Bulletin No. A300-53-6176 before next flight.

and

No further action.

<2> If crack is found in area 1 or area 2:

NOTE: If crack is higher than 30 mm (1.181 in.):

- Inform AIRBUS and send the affected Frame

foot for laboratory investigation.

- Perform the following steps.

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 80

5

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

SERVICE BULLETIN

<a> Apply Service Bulletin No. A300-53-6176 before next flight.

and

No further action.

OR

<b> Replace the cracked Frame foot at Frame 41 on LH side

before next flight, in accordance with TASK 536177-833-801

001 Repair .

and

Repeat the inspection of the replaced Frame foot at Frame 41

on LH side, at the threshold given in the table 2 of the planning

information paragraph E.(2).

(b) Send inspection report to AIRBUS, refer to Fig. A-FRAAA.

(2) Subtask 536177-832-002-001 - Do a Detailed Inspection of the Frame Foot at FR41

on RH Side

Work Zones and Access Panels

Zone Access/Work location

148 Access Door 147BZ

Work location Frame 41

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Non Aqueous Cleaner -

General

08BAA9 As required

References

Drawing R53810329

Service Bulletin (SB) A300-53-6111

A300-53-6176

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 81

5

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

SERVICE BULLETIN

References

Fig. A-FBAAA

Inspection areas

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

Fig. A-FRAAA

Inspection report

Sheet 01

Sheet 02

Fig. A-FFBAA

Flow Chart for Frame 41 on RH side

Sheet 01

Sheet 02

Sheet 03

Sheet 04

(a) At threshold given in the PLANNING INFORMATION Paragraph E.(2):

Do a detailed inspection of the Frame foot at Frame 41 on RH side.

Refer to Fig. A-FFBAA

Refer to Fig. A-FBAAA Sheet 01, Fig. A-FBAAA Sheet 02 and Fig. A-FBAAA Sheet

08

1 The Frame have never been inspected as per Service Bulletin No.

A300-53-6111 or never be repaired as per Service Bulletin No. A300-53-6111

or never be repaired as per R53810329:

a Clean the inspected areas with:

Non Aqueous

Cleaner - General

08BAA9 As required

b Do a detailed inspection of the area 1 and the area 2 of Frame foot at

Frame 41 on RH side.

<1> If crack is not found in area 1 or area 2:

<a> Repeat the inspection of the Frame foot at Frame 41 on RH

side, at the interval given in the table 2 of the planning

information paragraph E.(2).

OR

<b> Apply Service Bulletin No. A300-53-6176 before next flight.

and

No further action.

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 82

5

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

SERVICE BULLETIN

<2> If crack is found in area 1 or area 2:

NOTE: If crack is higher than 30 mm (1.181 in.):

- Inform AIRBUS and send the affected Frame

foot for laboratory investigation.

- Perform the following steps.

<a> Apply Service Bulletin No. A300-53-6176 before next flight.

and

No further action.

OR

<b> Replace the cracked Frame foot at Frame 41 on RH side

before next flight, in accordance with TASK 536177-833-801

001 Repair .

and

Repeat the inspection of the replaced Frame foot at Frame 41

on RH side, at the threshold given in the table 2 of the planning

information paragraph E.(2).

(b) Send inspection report to AIRBUS, refer to Fig. A-FRAAA.

(3) Subtask 536177-832-003-001 - Do a Detailed Inspection of the Frame Foot at FR42

on LH Side

Work Zones and Access Panels

Zone Access/Work location

147 Access Door 147BZ

Work location Frame 42

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Non Aqueous Cleaner -

General

08BAA9 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 83

5

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

SERVICE BULLETIN

References

Drawing R53810330

Service Bulletin (SB) A300-53-6111

A300-53-6176

Fig. A-FBAAA

Inspection areas

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

Fig. A-FRAAA

Inspection report

Sheet 01

Sheet 02

Fig. A-FFCAA

Flow Chart for Frame 42 on LH side

Sheet 01

Sheet 02

Sheet 03

Sheet 04

(a) At threshold given in the PLANNING INFORMATION Paragraph E.(2):

Do a detailed inspection of the Frame foot at Frame 42 on LH side.

Refer to Fig. A-FFCAA

Refer to Fig. A-FBAAA Sheet 01, Fig. A-FBAAA Sheet 03 and Fig. A-FBAAA Sheet

08

1 The Frame have never been inspected as per Service Bulletin No.

A300-53-6111 or never be repaired as per Service Bulletin No. A300-53-6111

or never be repaired as per R53810330:

a Clean the inspected areas with:

Non Aqueous

Cleaner - General

08BAA9 As required

b Do a detailed inspection of the area 1 and the area 2 of Frame foot at

Frame 42 on LH side.

<1> If crack is not found in area 1 or area 2:

<a> Repeat the inspection of the Frame foot at Frame 42 on LH

side, at the interval given in the table 2 of the planning

information paragraph E.(2).

OR

<b> Apply Service Bulletin No. A300-53-6176 before next flight.

and

No further action.

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 84

5

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

SERVICE BULLETIN

<2> If crack is found in area 1 or area 2:

NOTE: If crack is higher than 30 mm (1.181 in.):

- Inform AIRBUS and send the affected Frame

foot for laboratory investigation.

- Perform the following steps.

<a> Apply Service Bulletin No. A300-53-6176 before next flight.

and

No further action.

OR

<b> Replace the cracked Frame foot at Frame 42 on LH side

before next flight, in accordance with TASK 536177-833-801

001 Repair .

and

Repeat the inspection of the replaced Frame foot at Frame 42

on LH side, at the threshold given in the table 2 of the planning

information paragraph E.(2).

(b) Send inspection report to AIRBUS, refer to Fig. A-FRAAA.

(4) Subtask 536177-832-004-001 - Do a Detailed Inspection of the Frame Foot at FR42

on RH Side

Work Zones and Access Panels

Zone Access/Work location

148 Access Door 147BZ

Work location Frame 42

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Non Aqueous Cleaner -

General

08BAA9 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 85

5

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

SERVICE BULLETIN

References

Drawing R53810330

Service Bulletin (SB) A300-53-6111

A300-53-6176

Fig. A-FBAAA

Inspection areas

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

Fig. A-FFDAA

Flow Chart for Frame 42 on RH side

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Fig. A-FRAAA

Inspection report

Sheet 01

Sheet 02

(a) At threshold given in the PLANNING INFORMATION Paragraph E.(2):

Do a detailed inspection of the Frame foot at Frame 42 on RH side.

Refer to Fig. A-FFDAA

Refer to Fig. A-FBAAA Sheet 01, Fig. A-FBAAA Sheet 03 and Fig. A-FBAAA Sheet

08

1 The Frame have never been inspected as per Service Bulletin No.

A300-53-6111 or never be repaired as per Service Bulletin No. A300-53-6111

or never be repaired as per R53810330:

a Clean the inspected areas with:

Non Aqueous

Cleaner - General

08BAA9 As required

b Do a detailed inspection of the area 1 and the area 2 of Frame foot at

Frame 42 on RH side.

<1> If crack is not found in area 1 or area 2:

<a> Repeat the inspection of the Frame foot at Frame 42 on RH

side, at the interval given in the table 2 of the planning

information paragraph E.(2).

OR

<b> Apply Service Bulletin No. A300-53-6176 before next flight.

and

No further action.

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 86

5

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

SERVICE BULLETIN

<2> If crack is found in area 1 or area 2:

NOTE: If crack is higher than 30 mm (1.181 in.):

- Inform AIRBUS and send the affected Frame

foot for laboratory investigation.

- Perform the following steps.

<a> Apply Service Bulletin No. A300-53-6176 before next flight.

and

No further action.

OR

<b> Replace the cracked Frame foot at Frame 42 on RH side

before next flight, in accordance with TASK 536177-833-801

001 Repair .

and

Repeat the inspection of the replaced Frame foot at Frame 42

on RH side, at the threshold given in the table 2 of the planning

information paragraph E.(2).

(b) Send inspection report to AIRBUS, refer to Fig. A-FRAAA.

(5) Subtask 536177-832-005-001 - Do a Detailed Inspection of the Frame Foot at FR43

on LH Side

Work Zones and Access Panels

Zone Access/Work location

147 Access Door 147BZ

Work location Frame 43

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Non Aqueous Cleaner -

General

08BAA9 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 87

5

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

SERVICE BULLETIN

References

Drawing R53810331

Service Bulletin (SB) A300-53-6111

A300-53-6176

Fig. A-FBAAA

Inspection areas

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

Fig. A-FRAAA

Inspection report

Sheet 01

Sheet 02

Fig. A-FFEAA

Flow Chart for Frame 43 on LH side

Sheet 01

Sheet 02

Sheet 03

Sheet 04

(a) At threshold given in the PLANNING INFORMATION Paragraph E.(2):

Do a detailed inspection of the Frame foot at Frame 43 on LH side.

Refer to Fig. A-FFEAA

Refer to Fig. A-FBAAA Sheet 01, Fig. A-FBAAA Sheet 04 and Fig. A-FBAAA Sheet

08

1 The Frame have never been inspected as per Service Bulletin No.

A300-53-6111 or never be repaired as per Service Bulletin No. A300-53-6111

or never be repaired as per R53810331.

a Clean the inspected areas with:

Non Aqueous

Cleaner - General

08BAA9 As required

b Do a detailed inspection of the area 1 and the area 2 of Frame foot at

Frame 43 on LH side.

<1> If crack is not found in area 1 or area 2:

<a> Repeat the inspection of the Frame foot at Frame 43 on LH

side, at the interval given in the table 2 of the planning

information paragraph E.(2).

OR

<b> Apply Service Bulletin No. A300-53-6176 before next flight.

and

No further action.

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 88

5

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

SERVICE BULLETIN

<2> If crack is found in area 1 or area 2:

NOTE: If crack is higher than 30 mm (1.181 in.):

- Inform AIRBUS and send the affected Frame

foot for laboratory investigation.

- Perform the following steps.

<a> Apply Service Bulletin No. A300-53-6176 before next flight.

and

No further action.

OR

<b> Replace the cracked Frame foot at Frame 43 on LH side

before next flight, in accordance with TASK 536177-833-801

001 Repair .

and

Repeat the inspection of the replaced Frame foot at Frame 43

on LH side, at the threshold given in the table 2 of the planning

information paragraph E.(2).

(b) Send inspection report to AIRBUS, refer to Fig. A-FRAAA.

(6) Subtask 536177-832-006-001 - Do a Detailed Inspection of the Frame Foot at FR43

on RH Side

Work Zones and Access Panels

Zone Access/Work location

148 Access Door 147BZ

Work location Frame 43

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Non Aqueous Cleaner -

General

08BAA9 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 89

5

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

SERVICE BULLETIN

References

Drawing R53810331

Service Bulletin (SB) A300-53-6111

A300-53-6176

Fig. A-FBAAA

Inspection areas

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

Fig. A-FRAAA

Inspection report

Sheet 01

Sheet 02

Fig. A-FFFAA

Flow Chart for Frame 43 on RH side

Sheet 01

Sheet 02

Sheet 03

Sheet 04

(a) At threshold given in the PLANNING INFORMATION Paragraph E.(2):

Do a detailed inspection of the Frame foot at Frame 43 on RH side.

Refer to Fig. A-FFFAA

Refer to Fig. A-FBAAA Sheet 01, Fig. A-FBAAA Sheet 04 and Fig. A-FBAAA Sheet

08

1 The Frame have never been inspected as per Service Bulletin No.

A300-53-6111 or never be repaired as per Service Bulletin No. A300-53-6111

or never be repaired as per R53810331:

a Clean the inspected areas with:

Non Aqueous

Cleaner - General

08BAA9 As required

b Do a detailed inspection of the area 1 and the area 2 of Frame foot at

Frame 43 on RH side.

<1> If crack is not found in area 1 or area 2:

<a> Repeat the inspection of the Frame foot at Frame 43 on RH

side, at the interval given in the table 2 of the planning

information paragraph E.(2).

OR

<b> Apply Service Bulletin No. A300-53-6176 before next flight.

and

No further action.

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 90

5

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

SERVICE BULLETIN

<2> If crack is found in area 1 or area 2:

NOTE: If crack is higher than 30 mm (1.181 in.):

- Inform AIRBUS and send the affected Frame

foot for laboratory investigation.

- Perform the following steps.

<a> Apply Service Bulletin No. A300-53-6176 before next flight.

and

No further action.

OR

<b> Replace the cracked Frame foot at Frame 43 on RH side

before next flight, in accordance with TASK 536177-833-801

001 Repair .

and

Repeat the inspection of the replaced Frame foot at Frame 43

on RH side, at the threshold given in the table 2 of the planning

information paragraph E.(2).

(b) Send inspection report to AIRBUS, refer to Fig. A-FRAAA.

(7) Subtask 536177-832-007-001 - Do a Detailed Inspection of the Frame Foot at FR44

on LH Side

Work Zones and Access Panels

Zone Access/Work location

147 Access Door 147BZ

Work location Frame 44

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Non Aqueous Cleaner -

General

08BAA9 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 91

5

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

SERVICE BULLETIN

References

Drawing R53810332

Service Bulletin (SB) A300-53-6111

A300-53-6176

Fig. A-FBAAA

Inspection areas

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

Fig. A-FRAAA

Inspection report

Sheet 01

Sheet 02

Fig. A-FFGAA

Flow Chart for Frame 44 on LH side

Sheet 01

Sheet 02

Sheet 03

Sheet 04

(a) At threshold given in the PLANNING INFORMATION Paragraph E.(2):

Do a detailed inspection of the Frame foot at Frame 44 on LH side.

Refer to Fig. A-FFGAA

Refer to Fig. A-FBAAA Sheet 01, Fig. A-FBAAA Sheet 05 and Fig. A-FBAAA Sheet

08

1 The Frame have never been inspected as per Service Bulletin No.

A300-53-6111 or never be repaired as per Service Bulletin No. A300-53-6111

or never be repaired as per R53810332:

a Clean the inspected areas with:

Non Aqueous

Cleaner - General

08BAA9 As required

b Do a detailed inspection of the area 1 and the area 2 of Frame foot at

Frame 44 on LH side.

<1> If crack is not found in area 1 or area 2:

<a> Repeat the inspection of the Frame foot at Frame 44 on LH

side, at the interval given in the table 2 of the planning

information paragraph E.(2).

OR

<b> Apply Service Bulletin No. A300-53-6176 before next flight.

and

No further action.

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 92

5

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

SERVICE BULLETIN

<2> If crack is found in area 1 or area 2:

NOTE: If crack is higher than 30 mm (1.181 in.):

- Inform AIRBUS and send the affected Frame

foot for laboratory investigation.

- Perform the following steps.

<a> Apply Service Bulletin No. A300-53-6176 before next flight.

and

No further action.

OR

<b> Replace the cracked Frame foot at Frame 44 on LH side

before next flight, in accordance with TASK 536177-833-801

001 Repair .

and

Repeat the inspection of the replaced Frame foot at Frame 44

on LH side, at the threshold given in the table 2 of the planning

information paragraph E.(2).

(b) Send inspection report to AIRBUS, refer to Fig. A-FRAAA.

(8) Subtask 536177-832-008-001 - Do a Detailed Inspection of the Frame Foot at FR44

on RH Side

Work Zones and Access Panels

Zone Access/Work location

148 Access Door 147BZ

Work location Frame 44

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Non Aqueous Cleaner -

General

08BAA9 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 93

5

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

SERVICE BULLETIN

References

Drawing R53810332

Service Bulletin (SB) A300-53-6111

A300-53-6176

Fig. A-FBAAA

Inspection areas

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

Fig. A-FRAAA

Inspection report

Sheet 01

Sheet 02

Fig. A-FFHAA

Flow Chart for Frame 44 on RH side

Sheet 01

Sheet 02

Sheet 03

Sheet 04

(a) At threshold given in the PLANNING INFORMATION Paragraph E.(2):

Do a detailed inspection of the Frame foot at Frame 44 on RH side.

Refer to Fig. A-FFHAA

Refer to Fig. A-FBAAA Sheet 01, Fig. A-FBAAA Sheet 05 and Fig. A-FBAAA Sheet

08

1 The Frame have never been inspected as per Service Bulletin No.

A300-53-6111 or never be repaired as per Service Bulletin No. A300-53-6111

or never be repaired as per R53810332:

a Clean the inspected areas with:

Non Aqueous

Cleaner - General

08BAA9 As required

b Do a detailed inspection of the area 1 and the area 2 of Frame foot at

Frame 44 on RH side.

<1> If crack is not found in area 1 or area 2:

<a> Repeat the inspection of the Frame foot at Frame 44 on RH

side, at the interval given in the table 2 of the planning

information paragraph E.(2).

OR

<b> Apply Service Bulletin No. A300-53-6176 before next flight.

and

No further action.

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 94

5

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

SERVICE BULLETIN

<2> If crack is found in area 1 or area 2:

NOTE: If crack is higher than 30 mm (1.181 in.):

- Inform AIRBUS and send the affected Frame

foot for laboratory investigation.

- Perform the following steps.

<a> Apply Service Bulletin No. A300-53-6176 before next flight.

and

No further action.

OR

<b> Replace the cracked Frame foot at Frame 44 on RH side

before next flight, in accordance with TASK 536177-833-801

001 Repair .

and

Repeat the inspection of the replaced Frame foot at Frame 44

on RH side, at the threshold given in the table 2 of the planning

information paragraph E.(2).

(b) Send inspection report to AIRBUS, refer to Fig. A-FRAAA.

(9) Subtask 536177-832-009-001 - Do a Detailed Inspection of the Frame Foot at FR45

on LH Side

Work Zones and Access Panels

Zone Access/Work location

147 Access Door 147BZ

Work location Frame 45

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Non Aqueous Cleaner -

General

08BAA9 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 95

5

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

SERVICE BULLETIN

References

Drawing R53810322

Service Bulletin (SB) A300-53-6111

A300-53-6176

Fig. A-FBAAA

Inspection areas

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

Fig. A-FFIAA

Flow Chart for Frame 45 on LH side

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Fig. A-FRAAA

Inspection report

Sheet 01

Sheet 02

(a) At threshold given in the PLANNING INFORMATION Paragraph E.(2):

Do a detailed inspection of the Frame foot at Frame 45 on LH side.

Refer to Fig. A-FFIAA

Refer to Fig. A-FBAAA Sheet 01, Fig. A-FBAAA Sheet 06 and Fig. A-FBAAA Sheet

08

1 The Frame have never been inspected as per Service Bulletin No.

A300-53-6111 or never be repaired as per Service Bulletin No. A300-53-6111

or never be repaired as per R53810322:

a Clean the inspected areas with:

Non Aqueous

Cleaner - General

08BAA9 As required

b Do a detailed inspection of the area 1 and the area 2 of Frame foot at

Frame 45 on LH side.

<1> If crack is not found in area 1 or area 2:

<a> Repeat the inspection of the Frame foot at Frame 45 on LH

side, at the interval given in the table 2 of the planning

information paragraph E.(2).

OR

<b> Apply Service Bulletin No. A300-53-6176 before next flight.

and

No further action.

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 96

5

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

SERVICE BULLETIN

<2> If crack is found in area 1 or area 2:

NOTE: If crack is higher than 30 mm (1.181 in.):

- Inform AIRBUS and send the affected Frame

foot for laboratory investigation.

- Perform the following steps.

<a> Apply Service Bulletin No. A300-53-6176 before next flight.

and

No further action.

OR

<b> Replace the cracked Frame foot at Frame 45 on LH side

before next flight, in accordance with TASK 536177-833-801

001 Repair .

and

Repeat the inspection of the replaced Frame foot at Frame 45

on LH side, at the threshold given in the table 2 of the planning

information paragraph E.(2).

(b) Send inspection report to AIRBUS, refer to Fig. A-FRAAA.

(10) Subtask 536177-832-010-001 - Do a Detailed Inspection of the Frame Foot at FR45

on RH Side

Work Zones and Access Panels

Zone Access/Work location

148 Access Door 147BZ

Work location Frame 45

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Non Aqueous Cleaner -

General

08BAA9 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 97

5

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

SERVICE BULLETIN

References

Drawing R53810322

Service Bulletin (SB) A300-53-6111

A300-53-6176

Fig. A-FBAAA

Inspection areas

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

Fig. A-FFJAA

Flow Chart for Frame 45 on RH side

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Fig. A-FRAAA

Inspection report

Sheet 01

Sheet 02

(a) At threshold given in the PLANNING INFORMATION Paragraph E.(2):

Do a detailed inspection of the Frame foot at Frame 45 on RH side.

Refer to Fig. A-FFJAA

Refer to Fig. A-FBAAA Sheet 01, Fig. A-FBAAA Sheet 06 and Fig. A-FBAAA Sheet

08

1 The Frame have never been inspected as per Service Bulletin No.

A300-53-6111 or never be repaired as per Service Bulletin No. A300-53-6111

or never be repaired as per R53810322:

a Clean the inspected areas with:

Non Aqueous

Cleaner - General

08BAA9 As required

b Do a detailed inspection of the area 1 and the area 2 of Frame foot at

Frame 45 on RH side.

<1> If crack is not found in area 1 or area 2:

<a> Repeat the inspection of the Frame foot at Frame 45 on RH

side, at the interval given in the table 2 of the planning

information paragraph E.(2).

OR

<b> Apply Service Bulletin No. A300-53-6176 before next flight.

and

No further action.

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 98

5

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

SERVICE BULLETIN

<2> If crack is found in area 1 or area 2:

NOTE: If crack is higher than 30 mm (1.181 in.):

- Inform AIRBUS and send the affected Frame

foot for laboratory investigation.

- Perform the following steps.

<a> Apply Service Bulletin No. A300-53-6176 before next flight.

and

No further action.

OR

<b> Replace the cracked Frame foot at Frame 45 on RH side

before next flight, in accordance with TASK 536177-833-801

001 Repair .

and

Repeat the inspection of the replaced Frame foot at Frame 45

on RH side, at the threshold given in the table 2 of the planning

information paragraph E.(2).

(b) Send inspection report to AIRBUS, refer to Fig. A-FRAAA.

(11) Subtask 536177-832-011-001 - Do a Detailed Inspection of the Frame Foot at FR46

on LH Side

Work Zones and Access Panels

Zone Access/Work location

147 Access Door 147BZ

Work location Frame 46

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Non Aqueous Cleaner -

General

08BAA9 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 99

5

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

SERVICE BULLETIN

References

Drawing R53810323

Service Bulletin (SB) A300-53-6111

A300-53-6176

Fig. A-FBAAA

Inspection areas

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

Fig. A-FRAAA

Inspection report

Sheet 01

Sheet 02

Fig. A-FFKAA

Flow Chart for Frame 46 on LH side

Sheet 01

Sheet 02

Sheet 03

Sheet 04

(a) At threshold given in the PLANNING INFORMATION Paragraph E.(2):

Do a detailed inspection of the Frame foot at Frame 46 on LH side.

Refer to Fig. A-FFKAA

Refer to Fig. A-FBAAA Sheet 01, Fig. A-FBAAA Sheet 07 and Fig. A-FBAAA Sheet

08

1 The Frame have never been inspected as per Service Bulletin No.

A300-53-6111 or never be repaired as per Service Bulletin No. A300-53-6111

or never be repaired as per R53810323:

a Clean the inspected areas with:

Non Aqueous

Cleaner - General

08BAA9 As required

b Do a detailed inspection of the area 1 and the area 2 of Frame foot at

Frame 46 on LH side.

<1> If crack is not found in area 1 or area 2:

<a> Repeat the inspection of the Frame foot at Frame 46 on LH

side, at the interval given in the table 2 of the planning

information paragraph E.(2).

OR

<b> Apply Service Bulletin No. A300-53-6176 before next flight.

and

No further action.

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 100

5

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

SERVICE BULLETIN

<2> If crack is found in area 1 or area 2:

NOTE: If crack is higher than 30 mm (1.181 in.):

- Inform AIRBUS and send the affected Frame

foot for laboratory investigation.

- Perform the following steps.

<a> Apply Service Bulletin No. A300-53-6176 before next flight.

and

No further action.

OR

<b> Replace the cracked Frame foot at Frame 46 on LH side

before next flight, in accordance with TASK 536177-833-801

001 Repair .

and

Repeat the inspection of the replaced Frame foot at Frame 46

on LH side, at the threshold given in the table 2 of the planning

information paragraph E.(2).

(b) Send inspection report to AIRBUS, refer to Fig. A-FRAAA.

(12) Subtask 536177-832-012-001 - Do a Detailed Inspection of the Frame Foot at FR46

on RH Side

Work Zones and Access Panels

Zone Access/Work location

148 Access Door 147BZ

Work location Frame 46

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Non Aqueous Cleaner -

General

08BAA9 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 101

5

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

SERVICE BULLETIN

References

Drawing R53810323

Service Bulletin (SB) A300-53-6111

A300-53-6176

Fig. A-FBAAA

Inspection areas

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

Fig. A-FRAAA

Inspection report

Sheet 01

Sheet 02

Fig. A-FFLAA

Flow Chart for Frame 46 on RH side

Sheet 01

Sheet 02

Sheet 03

Sheet 04

(a) At threshold given in the PLANNING INFORMATION Paragraph E.(2):

Do a detailed inspection of the Frame foot at Frame 46 on RH side.

Refer to Fig. A-FFLAA

Refer to Fig. A-FBAAA Sheet 01, Fig. A-FBAAA Sheet 07 and Fig. A-FBAAA Sheet

08

1 The Frame have never been inspected as per Service Bulletin No.

A300-53-6111 or never be repaired as per Service Bulletin No. A300-53-6111

or never be repaired as per R53810323:

a Clean the inspected areas with:

Non Aqueous

Cleaner - General

08BAA9 As required

b Do a detailed inspection of the area 1 and the area 2 of Frame foot at

Frame 46 on RH side.

<1> If crack is not found in area 1 or area 2:

<a> Repeat the inspection of the Frame foot at Frame 46 on RH

side, at the interval given in the table 2 of the planning

information paragraph E.(2).

OR

<b> Apply Service Bulletin No. A300-53-6176 before next flight.

and

No further action.

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 102

5

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

SERVICE BULLETIN

<2> If crack is found in area 1 or area 2:

NOTE: If crack is higher than 30 mm (1.181 in.):

- Inform AIRBUS and send the affected Frame

foot for laboratory investigation.

- Perform the following steps.

<a> Apply Service Bulletin No. A300-53-6176 before next flight.

and

No further action.

OR

<b> Replace the cracked Frame foot at Frame 46 on RH side

before next flight, in accordance with TASK 536177-833-801

001 Repair .

and

Repeat the inspection of the replaced Frame foot at Frame 46

on RH side, at the threshold given in the table 2 of the planning

information paragraph E.(2).

(b) Send inspection report to AIRBUS, refer to Fig. A-FRAAA.

**CONF 002

(1) Subtask 536177-832-001-002 - Do a Detailed Inspection of the Frame Foot at FR41

on LH Side

Work Zones and Access Panels

Zone Access/Work location

147 Access Door 147BZ

Work location Frame 41

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Non Aqueous Cleaner -

General

08BAA9 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 103

5

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

SERVICE BULLETIN

References

Service Bulletin (SB) A300-53-6111

A300-53-6176

Fig. A-FBAAA

Inspection areas

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

Fig. A-FFAAA

Flow Chart for Frame 41 on LH side

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Fig. A-FRAAA

Inspection report

Sheet 01

Sheet 02

(a) At threshold given in the PLANNING INFORMATION Paragraph E.(2):

Do a detailed inspection of the Frame foot at Frame 41 on LH side.

Refer to Fig. A-FFAAA

Refer to Fig. A-FBAAA Sheet 01, Fig. A-FBAAA Sheet 02 and Fig. A-FBAAA Sheet

08

1 The Frame have been preventively repaired as per Service Bulletin No.

A300-53-6111:

a Clean the inspected areas with:

Non Aqueous

Cleaner - General

08BAA9 As required

b Do a detailed inspection of the area 1 and the area 2 of Frame foot at

Frame 41 on LH side.

<1> If crack is not found in area 1 or area 2:

<a> Repeat the inspection of the Frame foot at Frame 41 on LH

side, at the interval given in the table 3 of the planning

information paragraph E.(2).

OR

<b> Apply Service Bulletin No. A300-53-6176 before next flight.

and

No further action.

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 104

5

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

SERVICE BULLETIN

<2> If crack is found in area 1 or area 2:

NOTE: If crack is higher than 30 mm (1.181 in.):

- Inform AIRBUS and send the affected Frame

foot for laboratory investigation.

- Perform the following steps.

<a> Apply Service Bulletin No. A300-53-6176 before next flight.

and

No further action.

OR

<b> Replace the cracked Frame foot at Frame 41 on LH side

before next flight, in accordance with TASK 536177-833-801

001 Repair .

and

Repeat the inspection of the replaced Frame foot at Frame 41

on LH side, at the threshold given in the table 3 of the planning

information paragraph E.(2).

(b) Send inspection report to AIRBUS, refer to Fig. A-FRAAA.

(2) Subtask 536177-832-002-002 - Do a Detailed Inspection of the Frame Foot at FR41

on RH Side

Work Zones and Access Panels

Zone Access/Work location

148 Access Door 147BZ

Work location Frame 41

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Non Aqueous Cleaner -

General

08BAA9 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 105

5

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

SERVICE BULLETIN

References

Service Bulletin (SB) A300-53-6111

A300-53-6176

Fig. A-FBAAA

Inspection areas

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

Fig. A-FFBAA

Flow Chart for Frame 41 on RH side

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Fig. A-FRAAA

Inspection report

Sheet 01

Sheet 02

(a) At threshold given in the PLANNING INFORMATION Paragraph E.(2):

Do a detailed inspection of the Frame foot at Frame 41 on RH side.

Refer to Fig. A-FFBAA

Refer to Fig. A-FBAAA Sheet 01, Fig. A-FBAAA Sheet 02 and Fig. A-FBAAA Sheet

08

1 The Frame have been preventively repaired as per Service Bulletin No.

A300-53-6111:

a Clean the inspected areas with:

Non Aqueous

Cleaner - General

08BAA9 As required

b Do a detailed inspection of the area 1 and the area 2 of Frame foot at

Frame 41 on RH side.

<1> If crack is not found in area 1 or area 2:

<a> Repeat the inspection of the Frame foot at Frame 41 on RH

side, at the interval given in the table 3 of the planning

information paragraph E.(2).

OR

<b> Apply Service Bulletin No. A300-53-6176 before next flight.

and

No further action.

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 106

5

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

SERVICE BULLETIN

<2> If crack is found in area 1 or area 2:

NOTE: If crack is higher than 30 mm (1.181 in.):

- Inform AIRBUS and send the affected Frame

foot for laboratory investigation.

- Perform the following steps.

<a> Apply Service Bulletin No. A300-53-6176 before next flight.

and

No further action.

OR

<b> Replace the cracked Frame foot at Frame 41 on RH side

before next flight, in accordance with TASK 536177-833-801

001 Repair .

and

Repeat the inspection of the replaced Frame foot at Frame 41

on RH side, at the threshold given in the table 3 of the planning

information paragraph E.(2).

(b) Send inspection report to AIRBUS, refer to Fig. A-FRAAA.

(3) Subtask 536177-832-003-002 - Do a Detailed Inspection of the Frame Foot at FR42

on LH Side

Work Zones and Access Panels

Zone Access/Work location

147 Access Door 147BZ

Work location Frame 42

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Non Aqueous Cleaner -

General

08BAA9 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 107

5

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

SERVICE BULLETIN

References

Service Bulletin (SB) A300-53-6111

A300-53-6176

Fig. A-FBAAA

Inspection areas

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

Fig. A-FFCAA

Flow Chart for Frame 42 on LH side

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Fig. A-FRAAA

Inspection report

Sheet 01

Sheet 02

(a) At threshold given in the PLANNING INFORMATION Paragraph E.(2):

Do a detailed inspection of the Frame foot at Frame 42 on LH side.

Refer to Fig. A-FFCAA

Refer to Fig. A-FBAAA Sheet 01, Fig. A-FBAAA Sheet 03 and Fig. A-FBAAA Sheet

08

1 The Frame have been preventively repaired as per Service Bulletin No.

A300-53-6111:

a Clean the inspected areas with:

Non Aqueous

Cleaner - General

08BAA9 As required

b Do a detailed inspection of the area 1 and the area 2 of Frame foot at

Frame 42 on LH side.

<1> If crack is not found in area 1 or area 2:

<a> Repeat the inspection of the Frame foot at Frame 42 on LH

side, at the interval given in the table 3 of the planning

information paragraph E.(2).

OR

<b> Apply Service Bulletin No. A300-53-6176 before next flight.

and

No further action.

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 108

5

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

SERVICE BULLETIN

<2> If crack is found in area 1 or area 2:

NOTE: If crack is higher than 30 mm (1.181 in.):

- Inform AIRBUS and send the affected Frame

foot for laboratory investigation.

- Perform the following steps.

<a> Apply Service Bulletin No. A300-53-6176 before next flight.

and

No further action.

OR

<b> Replace the cracked Frame foot at Frame 42 on LH side

before next flight, in accordance with TASK 536177-833-801

001 Repair .

and

Repeat the inspection of the replaced Frame foot at Frame 42

on LH side, at the threshold given in the table 3 of the planning

information paragraph E.(2).

(b) Send inspection report to AIRBUS, refer to Fig. A-FRAAA.

(4) Subtask 536177-832-004-002 - Do a Detailed Inspection of the Frame Foot at FR42

on RH Side

Work Zones and Access Panels

Zone Access/Work location

148 Access Door 147BZ

Work location Frame 42

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Non Aqueous Cleaner -

General

08BAA9 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 109

5

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

SERVICE BULLETIN

References

Service Bulletin (SB) A300-53-6111

A300-53-6176

Fig. A-FBAAA

Inspection areas

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

Fig. A-FRAAA

Inspection report

Sheet 01

Sheet 02

Fig. A-FFDAA

Flow Chart for Frame 42 on RH side

Sheet 01

Sheet 02

Sheet 03

Sheet 04

(a) At threshold given in the PLANNING INFORMATION Paragraph E.(2):

Do a detailed inspection of the Frame foot at Frame 42 on RH side.

Refer to Fig. A-FFDAA

Refer to Fig. A-FBAAA Sheet 01, Fig. A-FBAAA Sheet 03 and Fig. A-FBAAA Sheet

08

1 The Frame have been preventively repaired as per Service Bulletin No.

A300-53-6111:

a Clean the inspected areas with:

Non Aqueous

Cleaner - General

08BAA9 As required

b Do a detailed inspection of the area 1 and the area 2 of Frame foot at

Frame 42 on RH side.

<1> If crack is not found in area 1 or area 2:

<a> Repeat the inspection of the Frame foot at Frame 42 on RH

side, at the interval given in the table 3 of the planning

information paragraph E.(2).

OR

<b> Apply Service Bulletin No. A300-53-6176 before next flight.

and

No further action.

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 110

5

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

SERVICE BULLETIN

<2> If crack is found in area 1 or area 2:

NOTE: If crack is higher than 30 mm (1.181 in.):

- Inform AIRBUS and send the affected Frame

foot for laboratory investigation.

- Perform the following steps.

<a> Apply Service Bulletin No. A300-53-6176 before next flight.

and

No further action.

OR

<b> Replace the cracked Frame foot at Frame 42 on RH side

before next flight, in accordance with TASK 536177-833-801

001 Repair .

and

Repeat the inspection of the replaced Frame foot at Frame 42

on RH side, at the threshold given in the table 3 of the planning

information paragraph E.(2).

(b) Send inspection report to AIRBUS, refer to Fig. A-FRAAA.

(5) Subtask 536177-832-005-002 - Do a Detailed Inspection of the Frame Foot at FR43

on LH Side

Work Zones and Access Panels

Zone Access/Work location

147 Access Door 147BZ

Work location Frame 43

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Non Aqueous Cleaner -

General

08BAA9 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 111

5

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

SERVICE BULLETIN

References

Service Bulletin (SB) A300-53-6111

A300-53-6176

Fig. A-FBAAA

Inspection areas

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

Fig. A-FFEAA

Flow Chart for Frame 43 on LH side

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Fig. A-FRAAA

Inspection report

Sheet 01

Sheet 02

(a) At threshold given in the PLANNING INFORMATION Paragraph E.(2):

Do a detailed inspection of the Frame foot at Frame 43 on LH side.

Refer to Fig. A-FFEAA

Refer to Fig. A-FBAAA Sheet 01, Fig. A-FBAAA Sheet 04 and Fig. A-FBAAA Sheet

08

1 The Frame have been preventively repaired as per Service Bulletin No.

A300-53-6111:

a Clean the inspected areas with:

Non Aqueous

Cleaner - General

08BAA9 As required

b Do a detailed inspection of the area 1 and the area 2 of Frame foot at

Frame 43 on LH side.

<1> If crack is not found in area 1 or area 2:

<a> Repeat the inspection of the Frame foot at Frame 43 on LH

side, at the interval given in the table 3 of the planning

information paragraph E.(2).

OR

<b> Apply Service Bulletin No. A300-53-6176 before next flight.

and

No further action.

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 112

5

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

SERVICE BULLETIN

<2> If crack is found in area 1 or area 2:

NOTE: If crack is higher than 30 mm (1.181 in.):

- Inform AIRBUS and send the affected Frame

foot for laboratory investigation.

- Perform the following steps.

<a> Apply Service Bulletin No. A300-53-6176 before next flight.

and

No further action.

OR

<b> Replace the cracked Frame foot at Frame 43 on LH side

before next flight, in accordance with TASK 536177-833-801

001 Repair .

and

Repeat the inspection of the replaced Frame foot at Frame 43

on LH side, at the threshold given in the table 3 of the planning

information paragraph E.(2).

(b) Send inspection report to AIRBUS, refer to Fig. A-FRAAA.

(6) Subtask 536177-832-006-002 - Do a Detailed Inspection of the Frame Foot at FR43

on RH Side

Work Zones and Access Panels

Zone Access/Work location

148 Access Door 147BZ

Work location Frame 43

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Non Aqueous Cleaner -

General

08BAA9 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 113

5

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

SERVICE BULLETIN

References

Service Bulletin (SB) A300-53-6111

A300-53-6176

Fig. A-FBAAA

Inspection areas

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

Fig. A-FFFAA

Flow Chart for Frame 43 on RH side

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Fig. A-FRAAA

Inspection report

Sheet 01

Sheet 02

(a) At threshold given in the PLANNING INFORMATION Paragraph E.(2):

Do a detailed inspection of the Frame foot at Frame 43 on RH side.

Refer to Fig. A-FFFAA

Refer to Fig. A-FBAAA Sheet 01, Fig. A-FBAAA Sheet 04 and Fig. A-FBAAA Sheet

08

1 The Frame have been preventively repaired as per Service Bulletin No.

A300-53-6111:

a Clean the inspected areas with:

Non Aqueous

Cleaner - General

08BAA9 As required

b Do a detailed inspection of the area 1 and the area 2 of Frame foot at

Frame 43 on RH side.

<1> If crack is not found in area 1 or area 2:

<a> Repeat the inspection of the Frame foot at Frame 43 on RH

side, at the interval given in the table 3 of the planning

information paragraph E.(2).

OR

<b> Apply Service Bulletin No. A300-53-6176 before next flight.

and

No further action.

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 114

5

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

SERVICE BULLETIN

<2> If crack is found in area 1 or area 2:

NOTE: If crack is higher than 30 mm (1.181 in.):

- Inform AIRBUS and send the affected Frame

foot for laboratory investigation.

- Perform the following steps.

<a> Apply Service Bulletin No. A300-53-6176 before next flight.

and

No further action.

OR

<b> Replace the cracked Frame foot at Frame 43 on RH side

before next flight, in accordance with TASK 536177-833-801

001 Repair .

and

Repeat the inspection of the replaced Frame foot at Frame 43

on RH side, at the threshold given in the table 3 of the planning

information paragraph E.(2).

(b) Send inspection report to AIRBUS, refer to Fig. A-FRAAA.

(7) Subtask 536177-832-007-002 - Do a Detailed Inspection of the Frame Foot at FR44

on LH Side

Work Zones and Access Panels

Zone Access/Work location

147 Access Door 147BZ

Work location Frame 44

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Non Aqueous Cleaner -

General

08BAA9 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 115

5

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

SERVICE BULLETIN

References

Service Bulletin (SB) A300-53-6111

A300-53-6176

Fig. A-FBAAA

Inspection areas

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

Fig. A-FFGAA

Flow Chart for Frame 44 on LH side

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Fig. A-FRAAA

Inspection report

Sheet 01

Sheet 02

(a) At threshold given in the PLANNING INFORMATION Paragraph E.(2):

Do a detailed inspection of the Frame foot at Frame 44 on LH side.

Refer to Fig. A-FFGAA

Refer to Fig. A-FBAAA Sheet 01, Fig. A-FBAAA Sheet 05 and Fig. A-FBAAA Sheet

08

1 The Frame have been preventively repaired as per Service Bulletin No.

A300-53-6111:

a Clean the inspected areas with:

Non Aqueous

Cleaner - General

08BAA9 As required

b Do a detailed inspection of the area 1 and the area 2 of Frame foot at

Frame 44 on LH side.

<1> If crack is not found in area 1 or area 2:

<a> Repeat the inspection of the Frame foot at Frame 44 on LH

side, at the interval given in the table 3 of the planning

information paragraph E.(2).

OR

<b> Apply Service Bulletin No. A300-53-6176 before next flight.

and

No further action.

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 116

5

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

SERVICE BULLETIN

<2> If crack is found in area 1 or area 2:

NOTE: If crack is higher than 30 mm (1.181 in.):

- Inform AIRBUS and send the affected Frame

foot for laboratory investigation.

- Perform the following steps.

<a> Apply Service Bulletin No. A300-53-6176 before next flight.

and

No further action.

OR

<b> Replace the cracked Frame foot at Frame 44 on LH side

before next flight, in accordance with TASK 536177-833-801

001 Repair .

and

Repeat the inspection of the replaced Frame foot at Frame 44

on LH side, at the threshold given in the table 3 planning

information paragraph E.(2).

(b) Send inspection report to AIRBUS, refer to Fig. A-FRAAA.

(8) Subtask 536177-832-008-002 - Do a Detailed Inspection of the Frame Foot at FR44

on RH Side

Work Zones and Access Panels

Zone Access/Work location

148 Access Door 147BZ

Work location Frame 44

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Non Aqueous Cleaner -

General

08BAA9 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 117

5

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

SERVICE BULLETIN

References

Service Bulletin (SB) A300-53-6111

A300-53-6176

Fig. A-FBAAA

Inspection areas

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

Fig. A-FFHAA

Flow Chart for Frame 44 on RH side

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Fig. A-FRAAA

Inspection report

Sheet 01

Sheet 02

(a) At threshold given in the PLANNING INFORMATION Paragraph E.(2):

Do a detailed inspection of the Frame foot at Frame 44 on RH side.

Refer to Fig. A-FFHAA

Refer to Fig. A-FBAAA Sheet 01, Fig. A-FBAAA Sheet 05 and Fig. A-FBAAA Sheet

08

1 The Frame have been preventively repaired as per Service Bulletin No.

A300-53-6111:

a Clean the inspected areas with:

Non Aqueous

Cleaner - General

08BAA9 As required

b Do a detailed inspection of the area 1 and the area 2 of Frame foot at

Frame 44 on RH side.

<1> If crack is not found in area 1 or area 2:

<a> Repeat the inspection of the Frame foot at Frame 44 on RH

side, at the interval given in the table 3 of the planning

information paragraph E.(2).

OR

<b> Apply Service Bulletin No. A300-53-6176 before next flight.

and

No further action.

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 118

5

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

SERVICE BULLETIN

<2> If crack is found in area 1 or area 2:

NOTE: If crack is higher than 30 mm (1.181 in.):

- Inform AIRBUS and send the affected Frame

foot for laboratory investigation.

- Perform the following steps.

<a> Apply Service Bulletin No. A300-53-6176 before next flight.

and

No further action.

OR

<b> Replace the cracked Frame foot at Frame 44 on RH side

before next flight, in accordance with TASK 536177-833-801

001 Repair .

and

Repeat the inspection of the replaced Frame foot at Frame 44

on RH side, at the threshold given in the table 3 of the planning

information paragraph E.(2).

(b) Send inspection report to AIRBUS, refer to Fig. A-FRAAA.

(9) Subtask 536177-832-009-002 - Do a Detailed Inspection of the Frame Foot at FR45

on LH Side

Work Zones and Access Panels

Zone Access/Work location

147 Access Door 147BZ

Work location Frame 45

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Non Aqueous Cleaner -

General

08BAA9 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 119

5

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

SERVICE BULLETIN

References

Service Bulletin (SB) A300-53-6111

A300-53-6176

Fig. A-FBAAA

Inspection areas

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

Fig. A-FFIAA

Flow Chart for Frame 45 on LH side

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Fig. A-FRAAA

Inspection report

Sheet 01

Sheet 02

(a) At threshold given in the PLANNING INFORMATION Paragraph E.(2):

Do a detailed inspection of the Frame foot at Frame 45 on LH side.

Refer to Fig. A-FFIAA

Refer to Fig. A-FBAAA Sheet 01, Fig. A-FBAAA Sheet 06 and Fig. A-FBAAA Sheet

08

1 The Frame have been preventively repaired as per Service Bulletin No.

A300-53-6111:

a Clean the inspected areas with:

Non Aqueous

Cleaner - General

08BAA9 As required

b Do a detailed inspection of the area 1 and the area 2 of Frame foot at

Frame 45 on LH side.

<1> If crack is not found in area 1 or area 2:

<a> Repeat the inspection of the Frame foot at Frame 45 on LH

side, at the interval given in the table 3 of the planning

information paragraph E.(2).

OR

<b> Apply Service Bulletin No. A300-53-6176 before next flight.

and

No further action.

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 120

5

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

SERVICE BULLETIN

<2> If crack is found in area 1 or area 2:

NOTE: If crack is higher than 30 mm (1.181 in.):

- Inform AIRBUS and send the affected Frame

foot for laboratory investigation.

- Perform the following steps.

<a> Apply Service Bulletin No. A300-53-6176 before next flight.

and

No further action.

OR

<b> Replace the cracked Frame foot at Frame 45 on LH side

before next flight, in accordance with TASK 536177-833-801

001 Repair .

and

Repeat the inspection of the replaced Frame foot at Frame 45

on LH side, at the threshold given in the table 3 of the planning

information paragraph E.(2).

(b) Send inspection report to AIRBUS, refer to Fig. A-FRAAA.

(10) Subtask 536177-832-010-002 - Do a Detailed Inspection of the Frame Foot at FR45

on RH Side

Work Zones and Access Panels

Zone Access/Work location

148 Access Door 147AZ

Work location Frame 45

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Non Aqueous Cleaner -

General

08BAA9 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 121

5

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

SERVICE BULLETIN

References

Service Bulletin (SB) A300-53-6111

A300-53-6176

Fig. A-FFJAA

Flow Chart for Frame 45 on RH side

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Fig. A-FBAAA

Inspection areas

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

Fig. A-FRAAA

Inspection report

Sheet 01

Sheet 02

(a) At threshold given in the PLANNING INFORMATION Paragraph E.(2):

Do a detailed inspection of the Frame foot at Frame 45 on RH side.

Refer to Fig. A-FFJAA

Refer to Fig. A-FBAAA Sheet 01, Fig. A-FBAAA Sheet 06 and Fig. A-FBAAA Sheet

08

1 The Frame have been preventively repaired as per Service Bulletin No.

A300-53-6111:

a Clean the inspected areas with:

Non Aqueous

Cleaner - General

08BAA9 As required

b Do a detailed inspection of the area 1 and the area 2 of Frame foot at

Frame 45 on RH side.

<1> If crack is not found in area 1 or area 2:

<a> Repeat the inspection of the Frame foot at Frame 45 on RH

side, at the interval given in the table 3 of the planning

information paragraph E.(2).

OR

<b> Apply Service Bulletin No. A300-53-6176 before next flight.

and

No further action.

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 122

5

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

SERVICE BULLETIN

<2> If crack is found in area 1 or area 2:

NOTE: If crack is higher than 30 mm (1.181 in.):

- Inform AIRBUS and send the affected Frame

foot for laboratory investigation.

- Perform the following steps.

<a> Apply Service Bulletin No. A300-53-6176 before next flight.

and

No further action.

OR

<b> Replace the cracked Frame foot at Frame 45 on RH side

before next flight, in accordance with TASK 536177-833-801

001 Repair .

and

Repeat the inspection of the replaced Frame foot at Frame 45

on RH side, at the threshold given in the table 3 of the planning

information paragraph E.(2).

(b) Send inspection report to AIRBUS, refer to Fig. A-FRAAA.

(11) Subtask 536177-832-011-002 - Do a Detailed Inspection of the Frame Foot at FR46

on LH Side

Work Zones and Access Panels

Zone Access/Work location

147 Access Door 147BZ

Work location Frame 46

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Non Aqueous Cleaner -

General

08BAA9 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 123

5

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

SERVICE BULLETIN

References

Service Bulletin (SB) A300-53-6111

A300-53-6176

Fig. A-FBAAA

Inspection areas

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

Fig. A-FRAAA

Inspection report

Sheet 01

Sheet 02

Fig. A-FFKAA

Flow Chart for Frame 46 on LH side

Sheet 01

Sheet 02

Sheet 03

Sheet 04

(a) At threshold given in the PLANNING INFORMATION Paragraph E.(2):

Do a detailed inspection of the Frame foot at Frame 46 on LH side.

Refer to Fig. A-FFKAA

Refer to Fig. A-FBAAA Sheet 01, Fig. A-FBAAA Sheet 07 and Fig. A-FBAAA Sheet

08

1 The Frame have been preventively repaired as per Service Bulletin No.

A300-53-6111:

a Clean the inspected areas with:

Non Aqueous

Cleaner - General

08BAA9 As required

b Do a detailed inspection of the area 1 and the area 2 of Frame foot at

Frame 46 on LH side.

<1> If crack is not found in area 1 or area 2:

<a> Repeat the inspection of the Frame foot at Frame 46 on LH

side, at the interval given in the table 3 of the planning

information paragraph E.(2).

OR

<b> Apply Service Bulletin No. A300-53-6176 before next flight.

and

No further action.

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 124

5

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

SERVICE BULLETIN

<2> If crack is found in area 1 or area 2:

NOTE: If crack is higher than 30 mm (1.181 in.):

- Inform AIRBUS and send the affected Frame

foot for laboratory investigation.

- Perform the following steps.

<a> Apply Service Bulletin No. A300-53-6176 before next flight.

and

No further action.

OR

<b> Replace the cracked Frame foot at Frame 46 on LH side

before next flight, in accordance with TASK 536177-833-801

001 Repair .

and

Repeat the inspection of the replaced Frame foot at Frame 46

on LH side, at the threshold given in the table 3 of the planning

information paragraph E.(2).

(b) Send inspection report to AIRBUS, refer to Fig. A-FRAAA.

(12) Subtask 536177-832-012-002 - Do a Detailed Inspection of the Frame Foot at FR46

on RH Side

Work Zones and Access Panels

Zone Access/Work location

148 Access Door 147BZ

Work location Frame 46

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Non Aqueous Cleaner -

General

08BAA9 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 125

5

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

SERVICE BULLETIN

References

Service Bulletin (SB) A300-53-6111

A300-53-6176

Fig. A-FBAAA

Inspection areas

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

Fig. A-FRAAA

Inspection report

Sheet 01

Sheet 02

Fig. A-FFLAA

Flow Chart for Frame 46 on RH side

Sheet 01

Sheet 02

Sheet 03

Sheet 04

(a) At threshold given in the PLANNING INFORMATION Paragraph E.(2):

Do a detailed inspection of the Frame foot at Frame 46 on RH side.

Refer to Fig. A-FFLAA

Refer to Fig. A-FBAAA Sheet 01, Fig. A-FBAAA Sheet 07 and Fig. A-FBAAA Sheet

08

1 The Frame have been preventively repaired as per Service Bulletin No.

A300-53-6111:

a Clean the inspected areas with:

Non Aqueous

Cleaner - General

08BAA9 As required

b Do a detailed inspection of the area 1 and the area 2 of Frame foot at

Frame 46 on RH side.

<1> If crack is not found in area 1 or area 2:

<a> Repeat the inspection of the Frame foot at Frame 46 on RH

side, at the interval given in the table 3 of the planning

information paragraph E.(2).

OR

<b> Apply Service Bulletin No. A300-53-6176 before next flight.

and

No further action.

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 126

5

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

SERVICE BULLETIN

<2> If crack is found in area 1 or area 2:

NOTE: If crack is higher than 30 mm (1.181 in.):

- Inform AIRBUS and send the affected Frame

foot for laboratory investigation.

- Perform the following steps.

<a> Apply Service Bulletin No. A300-53-6176 before next flight.

and

No further action.

OR

<b> Replace the cracked Frame foot at Frame 46 on RH side

before next flight, in accordance with TASK 536177-833-801

001 Repair .

and

Repeat the inspection of the replaced Frame foot at Frame 46

on RH side, at the threshold given in the table 3 of the planning

information paragraph E.(2).

(b) Send inspection report to AIRBUS, refer to Fig. A-FRAAA.

**CONF 003

(1) Subtask 536177-832-001-003 - Do a Detailed Inspection of the Frame Foot at FR41

on LH Side

Work Zones and Access Panels

Zone Access/Work location

147 Access Door 147BZ

Work location Frame 41

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Non Aqueous Cleaner -

General

08BAA9 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 127

5

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

SERVICE BULLETIN

References

Drawing R53810329

Service Bulletin (SB) A300-53-6111

A300-53-6176

Fig. A-FFAAA

Flow Chart for Frame 41 on LH side

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Fig. A-FBAAA

Inspection areas

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

Fig. A-FRAAA

Inspection report

Sheet 01

Sheet 02

(a) At threshold given in the PLANNING INFORMATION Paragraph E.(2):

Do a detailed inspection of the Frame foot at Frame 41 on LH side.

Refer to Fig. A-FFAAA

Refer to Fig. A-FBAAA Sheet 01, Fig. A-FBAAA Sheet 02 and Fig. A-FBAAA Sheet

08

1 The Frame have been repaired in area 1 as per Service Bulletin No.

A300-53-6111 or R53810329:

a Clean the inspected areas with:

Non Aqueous

Cleaner - General

08BAA9 As required

b Do a detailed inspection of the area 2 of Frame foot at Frame 41 on LH

side.

<1> If crack is not found in area 2:

<a> Repeat the inspection of the Frame foot at Frame 41 on LH

side, at the interval given in the table 4 of the planning

information paragraph E.(2).

OR

<b> Apply Service Bulletin No. A300-53-6176 before next flight.

and

No further action.

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 128

5

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

SERVICE BULLETIN

<2> If crack is found in area 2:

NOTE: If crack is higher than 30 mm (1.181 in.):

- Inform AIRBUS and send the affected Frame

foot for laboratory investigation.

- Perform the following steps.

<a> Apply Service Bulletin No. A300-53-6176 before next flight.

and

No further action.

OR

<b> Replace the cracked Frame foot at Frame 41 on LH side

before next flight, in accordance with TASK 536177-833-801

001 Repair .

and

Repeat the inspection of the replaced Frame foot at Frame 41

on LH side, at the threshold given in the table 4 of the planning

information paragraph E.(2).

(b) Send inspection report to AIRBUS, refer to Fig. A-FRAAA.

(2) Subtask 536177-832-002-003 - Do a Detailed Inspection of the Frame Foot at FR41

on RH Side

Work Zones and Access Panels

Zone Access/Work location

148 Access Door 147BZ

Work location Frame 41

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Non Aqueous Cleaner -

General

08BAA9 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 129

5

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

SERVICE BULLETIN

References

Drawing R53810329

Service Bulletin (SB) A300-53-6111

A300-53-6176

Fig. A-FBAAA

Inspection areas

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

Fig. A-FFBAA

Flow Chart for Frame 41 on RH side

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Fig. A-FRAAA

Inspection report

Sheet 01

Sheet 02

(a) At threshold given in the PLANNING INFORMATION Paragraph E.(2):

Do a detailed inspection of the Frame foot at Frame 41 on RH side.

Refer to Fig. A-FFBAA

Refer to Fig. A-FBAAA Sheet 01, Fig. A-FBAAA Sheet 02 and Fig. A-FBAAA Sheet

08

1 The Frame have been repaired in area 1 as per Service Bulletin No.

A300-53-6111 or R53810329:

a Clean the inspected areas with:

Non Aqueous

Cleaner - General

08BAA9 As required

b Do a detailed inspection of the area 2 of Frame foot at Frame 41 on RH

side.

<1> If crack is not found in area 2:

<a> Repeat the inspection of the Frame foot at Frame 41 on RH

side, at the interval given in the table 4 of the planning

information paragraph E.(2).

OR

<b> Apply Service Bulletin No. A300-53-6176 before next flight.

and

No further action.

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 130

5

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

SERVICE BULLETIN

<2> If crack is found in area 2:

NOTE: If crack is higher than 30 mm (1.181 in.):

- Inform AIRBUS and send the affected Frame

foot for laboratory investigation.

- Perform the following steps.

<a> Apply Service Bulletin No. A300-53-6176 before next flight.

and

No further action.

OR

<b> Replace the cracked Frame foot at Frame 41 on RH side

before next flight, in accordance with TASK 536177-833-801

001 Repair .

and

Repeat the inspection of the replaced Frame foot at Frame 41

on RH side, at the threshold given in the table 4 of the planning

information paragraph E.(2).

(b) Send inspection report to AIRBUS, refer to Fig. A-FRAAA.

(3) Subtask 536177-832-003-003 - Do a Detailed Inspection of the Frame Foot at FR42

on LH Side

Work Zones and Access Panels

Zone Access/Work location

147 Access Door 147BZ

Work location Frame 42

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Non Aqueous Cleaner -

General

08BAA9 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 131

5

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

SERVICE BULLETIN

References

Drawing R53810330

Service Bulletin (SB) A300-53-6111

A300-53-6176

Fig. A-FBAAA

Inspection areas

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

Fig. A-FFCAA

Flow Chart for Frame 42 on LH side

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Fig. A-FRAAA

Inspection report

Sheet 01

Sheet 02

(a) At threshold given in the PLANNING INFORMATION Paragraph E.(2):

Do a detailed inspection of the Frame foot at Frame 42 on LH side.

Refer to Fig. A-FFCAA

Refer to Fig. A-FBAAA Sheet 01, Fig. A-FBAAA Sheet 03 and Fig. A-FBAAA Sheet

08

1 The Frame have been repaired in area 1 as per Service Bulletin No.

A300-53-6111 or R53810330:

a Clean the inspected areas with:

Non Aqueous

Cleaner - General

08BAA9 As required

b Do a detailed inspection of the area 2 of Frame foot at Frame 42 on LH

side.

<1> If crack is not found in area 2:

<a> Repeat the inspection of the Frame foot at Frame 42 on LH

side, at the interval given in the table 4 of the planning

information paragraph E.(2).

OR

<b> Apply Service Bulletin No. A300-53-6176 before next flight.

and

No further action.

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 132

5

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

SERVICE BULLETIN

<2> If crack is found in area 2:

NOTE: If crack is higher than 30 mm (1.181 in.):

- Inform AIRBUS and send the affected Frame

foot for laboratory investigation.

- Perform the following steps.

<a> Apply Service Bulletin No. A300-53-6176 before next flight.

and

No further action.

OR

<b> Replace the cracked Frame foot at Frame 42 on LH side

before next flight, in accordance with TASK 536177-833-801

001 Repair .

and

Repeat the inspection of the replaced Frame foot at Frame 42

on LH side, at the threshold given in the table 4 of the planning

information paragraph E.(2).

(b) Send inspection report to AIRBUS, refer to Fig. A-FRAAA.

(4) Subtask 536177-832-004-003 - Do a Detailed Inspection of the Frame Foot at FR42

on RH Side

Work Zones and Access Panels

Zone Access/Work location

148 Access Door 147BZ

Work location Frame 42

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Non Aqueous Cleaner -

General

08BAA9 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 133

5

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

SERVICE BULLETIN

References

Drawing R53810330

Service Bulletin (SB) A300-53-6111

A300-53-6176

Fig. A-FBAAA

Inspection areas

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

Fig. A-FRAAA

Inspection report

Sheet 01

Sheet 02

Fig. A-FFDAA

Flow Chart for Frame 42 on RH side

Sheet 01

Sheet 02

Sheet 03

Sheet 04

(a) At threshold given in the PLANNING INFORMATION Paragraph E.(2):

Do a detailed inspection of the Frame foot at Frame 42 on RH side.

Refer to Fig. A-FFDAA

Refer to Fig. A-FBAAA Sheet 01, Fig. A-FBAAA Sheet 03 and Fig. A-FBAAA Sheet

08

1 The Frame have been repaired in area 1 as per Service Bulletin No.

A300-53-6111 or R53810330:

a Clean the inspected areas with:

Non Aqueous

Cleaner - General

08BAA9 As required

b Do a detailed inspection of the area 2 of Frame foot at Frame 42 on RH

side.

<1> If crack is not found in area 2:

<a> Repeat the inspection of the Frame foot at Frame 42 on RH

side, at the interval given in the table 4 of the planning

information paragraph E.(2).

OR

<b> Apply Service Bulletin No. A300-53-6176 before next flight.

and

No further action.

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 134

5

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

SERVICE BULLETIN

<2> If crack is found in area 2:

NOTE: If crack is higher than 30 mm (1.181 in.):

- Inform AIRBUS and send the affected Frame

foot for laboratory investigation.

- Perform the following steps.

<a> Apply Service Bulletin No. A300-53-6176 before next flight.

and

No further action.

OR

<b> Replace the cracked Frame foot at Frame 42 on RH side

before next flight, in accordance with TASK 536177-833-801

001 Repair .

and

Repeat the inspection of the replaced Frame foot at Frame 42

on RH side, at the threshold given in the table 4 of the planning

information paragraph E.(2).

(b) Send inspection report to AIRBUS, refer to Fig. A-FRAAA.

(5) Subtask 536177-832-005-003 - Do a Detailed Inspection of the Frame Foot at FR43

on LH Side

Work Zones and Access Panels

Zone Access/Work location

147 Access Door 147BZ

Work location Frame 43

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Non Aqueous Cleaner -

General

08BAA9 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 135

5

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

SERVICE BULLETIN

References

Drawing R53810331

Service Bulletin (SB) A300-53-6111

A300-53-6176

Fig. A-FBAAA

Inspection areas

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

Fig. A-FFEAA

Flow Chart for Frame 43 on LH side

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Fig. A-FRAAA

Inspection report

Sheet 01

Sheet 02

(a) At threshold given in the PLANNING INFORMATION Paragraph E.(2):

Do a detailed inspection of the Frame foot at Frame 43 on LH side.

Refer to Fig. A-FFEAA

Refer to Fig. A-FBAAA Sheet 01, Fig. A-FBAAA Sheet 04 and Fig. A-FBAAA Sheet

08

1 The Frame have been repaired in area 1 as per Service Bulletin No.

A300-53-6111 or R53810331:

a Clean the inspected areas with:

Non Aqueous

Cleaner - General

08BAA9 As required

b Do a detailed inspection of the area 2 of Frame foot at Frame 43 on LH

side.

<1> If crack is not found in area 2:

<a> Repeat the inspection of the Frame foot at Frame 43 on LH

side, at the interval given in the table 4 of the planning

information paragraph E.(2).

OR

<b> Apply Service Bulletin No. A300-53-6176 before next flight.

and

No further action.

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 136

5

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

SERVICE BULLETIN

<2> If crack is found in area 2:

NOTE: If crack is higher than 30 mm (1.181 in.):

- Inform AIRBUS and send the affected Frame

foot for laboratory investigation.

- Perform the following steps.

<a> Apply Service Bulletin No. A300-53-6176 before next flight.

and

No further action.

OR

<b> Replace the cracked Frame foot at Frame 43 on LH side

before next flight, in accordance with TASK 536177-833-801

001 Repair .

and

Repeat the inspection of the replaced Frame foot at Frame 43

on LH side, at the threshold given in the table 4 of the planning

information paragraph E.(2).

(b) Send inspection report to AIRBUS, refer to Fig. A-FRAAA.

(6) Subtask 536177-832-006-003 - Do a Detailed Inspection of the Frame Foot at FR43

on RH Side

Work Zones and Access Panels

Zone Access/Work location

148 Access Door 147BZ

Work location Frame 43

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Non Aqueous Cleaner -

General

08BAA9 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 137

5

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

SERVICE BULLETIN

References

Drawing R53810331

Service Bulletin (SB) A300-53-6111

A300-53-6176

Fig. A-FBAAA

Inspection areas

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

Fig. A-FFFAA

Flow Chart for Frame 43 on RH side

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Fig. A-FRAAA

Inspection report

Sheet 01

Sheet 02

(a) At threshold given in the PLANNING INFORMATION Paragraph E.(2):

Do a detailed inspection of the Frame foot at Frame 43 on RH side.

Refer to Fig. A-FFFAA

Refer to Fig. A-FBAAA Sheet 01, Fig. A-FBAAA Sheet 04 and Fig. A-FBAAA Sheet

08

1 The Frame have been repaired in area 1 as per Service Bulletin No.

A300-53-6111 or R53810331:

a Clean the inspected areas with:

Non Aqueous

Cleaner - General

08BAA9 As required

b Do a detailed inspection of the area 2 of Frame foot at Frame 43 on RH

side.

<1> If crack is not found in area 2:

<a> Repeat the inspection of the Frame foot at Frame 43 on RH

side, at the interval given in the table 4 of the planning

information paragraph E.(2).

OR

<b> Apply Service Bulletin No. A300-53-6176 before next flight.

and

No further action.

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 138

5

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

SERVICE BULLETIN

<2> If crack is found in area 2:

NOTE: If crack is higher than 30 mm (1.181 in.):

- Inform AIRBUS and send the affected Frame

foot for laboratory investigation.

- Perform the following steps.

<a> Apply Service Bulletin No. A300-53-6176 before next flight.

and

No further action.

OR

<b> Replace the cracked Frame foot at Frame 43 on RH side

before next flight, in accordance with TASK 536177-833-801

001 Repair .

and

Repeat the inspection of the replaced Frame foot at Frame 43

on RH side, at the threshold given in the table 4 of the planning

information paragraph E.(2).

(b) Send inspection report to AIRBUS, refer to Fig. A-FRAAA.

(7) Subtask 536177-832-007-003 - Do a Detailed Inspection of the Frame Foot at FR44

on LH Side

Work Zones and Access Panels

Zone Access/Work location

147 Access Door 147BZ

Work location Frame 44

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Non Aqueous Cleaner -

General

08BAA9 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 139

5

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

SERVICE BULLETIN

References

Drawing R53810332

Service Bulletin (SB) A300-53-6111

A300-53-6176

Fig. A-FBAAA

Inspection areas

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

Fig. A-FFGAA

Flow Chart for Frame 44 on LH side

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Fig. A-FRAAA

Inspection report

Sheet 01

Sheet 02

(a) At threshold given in the PLANNING INFORMATION Paragraph E.(2):

Do a detailed inspection of the Frame foot at Frame 44 on LH side.

Refer to Fig. A-FFGAA

Refer to Fig. A-FBAAA Sheet 01, Fig. A-FBAAA Sheet 05 and Fig. A-FBAAA Sheet

08

1 The Frame have been repaired in area 1 as per Service Bulletin No.

A300-53-6111 or R53810332:

a Clean the inspected areas with:

Non Aqueous

Cleaner - General

08BAA9 As required

b Do a detailed inspection of the area 2 of Frame foot at Frame 44 on LH

side.

<1> If crack is not found in area 2:

<a> Repeat the inspection of the Frame foot at Frame 44 on LH

side, at the interval given in the table 4 of the planning

information paragraph E.(2).

OR

<b> Apply Service Bulletin No. A300-53-6176 before next flight.

and

No further action.

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 140

5

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

SERVICE BULLETIN

<2> If crack is found in area 2:

NOTE: If crack is higher than 30 mm (1.181 in.):

- Inform AIRBUS and send the affected Frame

foot for laboratory investigation.

- Perform the following steps.

<a> Apply Service Bulletin No. A300-53-6176 before next flight.

and

No further action.

OR

<b> Replace the cracked Frame foot at Frame 44 on LH side

before next flight, in accordance with TASK 536177-833-801

001 Repair .

and

Repeat the inspection of the replaced Frame foot at Frame 44

on LH side, at the threshold given in the table 4 of the planning

information paragraph E.(2).

(b) Send inspection report to AIRBUS, refer to Fig. A-FRAAA.

(8) Subtask 536177-832-008-003 - Do a Detailed Inspection of the Frame Foot at FR44

on RH Side

Work Zones and Access Panels

Zone Access/Work location

148 Access Door 147BZ

Work location Frame 44

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Non Aqueous Cleaner -

General

08BAA9 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 141

5

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

SERVICE BULLETIN

References

Drawing R53810332

Service Bulletin (SB) A300-53-6111

A300-53-6176

Fig. A-FBAAA

Inspection areas

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

Fig. A-FFHAA

Flow Chart for Frame 44 on RH side

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Fig. A-FRAAA

Inspection report

Sheet 01

Sheet 02

(a) At threshold given in the PLANNING INFORMATION Paragraph E.(2):

Do a detailed inspection of the Frame foot at Frame 44 on RH side.

Refer to Fig. A-FFHAA

Refer to Fig. A-FBAAA Sheet 01, Fig. A-FBAAA Sheet 05 and Fig. A-FBAAA Sheet

08

1 The Frame have been repaired in area 1 as per Service Bulletin No.

A300-53-6111 or R53810332:

a Clean the inspected areas with:

Non Aqueous

Cleaner - General

08BAA9 As required

b Do a detailed inspection of the area 2 of Frame foot at Frame 44 on RH

side.

<1> If crack is not found in area 2:

<a> Repeat the inspection of the Frame foot at Frame 44 on RH

side, at the interval given in the table 4 of the planning

information paragraph E.(2).

OR

<b> Apply Service Bulletin No. A300-53-6176 before next flight.

and

No further action.

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 142

5

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

SERVICE BULLETIN

<2> If crack is found in area 2:

NOTE: If crack is higher than 30 mm (1.181 in.):

- Inform AIRBUS and send the affected Frame

foot for laboratory investigation.

- Perform the following steps.

<a> Apply Service Bulletin No. A300-53-6176 before next flight.

and

No further action.

OR

<b> Replace the cracked Frame foot at Frame 44 on RH side

before next flight, in accordance with TASK 536177-833-801

001 Repair .

and

Repeat the inspection of the replaced Frame foot at Frame 44

on RH side, at the threshold given in the table 4 of the planning

information paragraph E.(2).

(b) Send inspection report to AIRBUS, refer to Fig. A-FRAAA.

(9) Subtask 536177-832-009-003 - Do a Detailed Inspection of the Frame Foot at FR45

on LH Side

Work Zones and Access Panels

Zone Access/Work location

148 Access Door 147BZ

Work location Frame 45

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Non Aqueous Cleaner -

General

08BAA9 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 143

5

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

SERVICE BULLETIN

References

Drawing R53810322

Service Bulletin (SB) A300-53-6111

A300-53-6176

Fig. A-FBAAA

Inspection areas

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

Fig. A-FFIAA

Flow Chart for Frame 45 on LH side

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Fig. A-FRAAA

Inspection report

Sheet 01

Sheet 02

(a) At threshold given in the PLANNING INFORMATION Paragraph E.(2):

Do a detailed inspection of the Frame foot at Frame 45 on LH side.

Refer to Fig. A-FFIAA

Refer to Fig. A-FBAAA Sheet 01, Fig. A-FBAAA Sheet 06 and Fig. A-FBAAA Sheet

08

1 The Frame have been repaired in area 1 as per Service Bulletin No.

A300-53-6111 or R53810322:

a Clean the inspected areas with:

Non Aqueous

Cleaner - General

08BAA9 As required

b Do a detailed inspection of the area 2 of Frame foot at Frame 45 on LH

side.

<1> If crack is not found in area 2:

<a> Repeat the inspection of the Frame foot at Frame 45 on LH

side, at the interval given in the table 4 of the planning

information paragraph E.(2).

OR

<b> Apply Service Bulletin No. A300-53-6176 before next flight.

and

No further action.

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 144

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SERVICE BULLETIN

<2> If crack is found in area 2:

NOTE: If crack is higher than 30 mm (1.181 in.):

- Inform AIRBUS and send the affected Frame

foot for laboratory investigation.

- Perform the following steps.

<a> Apply Service Bulletin No. A300-53-6176 before next flight.

and

No further action.

OR

<b> Replace the cracked Frame foot at Frame 45 on LH side

before next flight, in accordance with TASK 536177-833-801

001 Repair .

and

Repeat the inspection of the replaced Frame foot at Frame 45

on LH side, at the threshold given in the table 4 of the planning

information paragraph E.(2).

(b) Send inspection report to AIRBUS, refer to Fig. A-FRAAA.

(10) Subtask 536177-832-010-003 - Do a Detailed Inspection of the Frame Foot at FR45

on RH Side

Work Zones and Access Panels

Zone Access/Work location

148 Access Door 147BZ

Work location Frame 45

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Non Aqueous Cleaner -

General

08BAA9 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 145

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SERVICE BULLETIN

References

Drawing R53810322

Service Bulletin (SB) A300-53-6111

A300-53-6176

Fig. A-FBAAA

Inspection areas

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

Fig. A-FFJAA

Flow Chart for Frame 45 on RH side

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Fig. A-FRAAA

Inspection report

Sheet 01

Sheet 02

(a) At threshold given in the PLANNING INFORMATION Paragraph E.(2):

Do a detailed inspection of the Frame foot at Frame 45 on RH side.

Refer to Fig. A-FFJAA

Refer to Fig. A-FBAAA Sheet 01, Fig. A-FBAAA Sheet 06 and Fig. A-FBAAA Sheet

08

1 The Frame have been repaired in area 1 as per Service Bulletin No.

A300-53-6111 or R53810322:

a Clean the inspected areas with:

Non Aqueous

Cleaner - General

08BAA9 As required

b Do a detailed inspection of the area 2 of Frame foot at Frame 45 on RH

side.

<1> If crack is not found in area 2:

<a> Repeat the inspection of the Frame foot at Frame 45 on RH

side, at the interval given in the table 4 of the planning

information paragraph E.(2).

OR

<b> Apply Service Bulletin No. A300-53-6176 before next flight.

and

No further action.

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 146

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@A300-600

SERVICE BULLETIN

<2> If crack is found in area 2:

NOTE: If crack is higher than 30 mm (1.181 in.):

- Inform AIRBUS and send the affected Frame

foot for laboratory investigation.

- Perform the following steps.

<a> Apply Service Bulletin No. A300-53-6176 before next flight.

and

No further action.

OR

<b> Replace the cracked Frame foot at Frame 45 on RH side

before next flight, in accordance with TASK 536177-833-801

001 Repair .

and

Repeat the inspection of the replaced Frame foot at Frame 45

on RH side, at the threshold given in the table 4 of the planning

information paragraph E.(2).

(b) Send inspection report to AIRBUS, refer to Fig. A-FRAAA.

(11) Subtask 536177-832-011-003 - Do a Detailed Inspection of the Frame Foot at FR46

on LH Side

Work Zones and Access Panels

Zone Access/Work location

147 Access Door 147BZ

Work location Frame 46

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Non Aqueous Cleaner -

General

08BAA9 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 147

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@A300-600

SERVICE BULLETIN

References

Drawing R53810323

Service Bulletin (SB) A300-53-6111

A300-53-6176

Fig. A-FBAAA

Inspection areas

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

Fig. A-FRAAA

Inspection report

Sheet 01

Sheet 02

Fig. A-FFKAA

Flow Chart for Frame 46 on LH side

Sheet 01

Sheet 02

Sheet 03

Sheet 04

(a) At threshold given in the PLANNING INFORMATION Paragraph E.(2):

Do a detailed inspection of the Frame foot at Frame 46 on LH side.

Refer to Fig. A-FFKAA

Refer to Fig. A-FBAAA Sheet 01, Fig. A-FBAAA Sheet 07 and Fig. A-FBAAA Sheet

08

1 The Frame have been repaired in area 1 as per Service Bulletin No.

A300-53-6111 or R53810323:

a Clean the inspected areas with:

Non Aqueous

Cleaner - General

08BAA9 As required

b Do a detailed inspection of the area 2 of Frame foot at Frame 46 on LH

side.

<1> If crack is not found in area 2:

<a> Repeat the inspection of the Frame foot at Frame 46 on LH

side, at the interval given in the table 4 of the planning

information paragraph E.(2).

OR

<b> Apply Service Bulletin No. A300-53-6176 before next flight.

and

No further action.

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 148

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@A300-600

SERVICE BULLETIN

<2> If crack is found in area 2:

NOTE: If crack is higher than 30 mm (1.181 in.):

- Inform AIRBUS and send the affected Frame

foot for laboratory investigation.

- Perform the following steps.

<a> Apply Service Bulletin No. A300-53-6176 before next flight.

and

No further action.

OR

<b> Replace the cracked Frame foot at Frame 46 on LH side

before next flight, in accordance with TASK 536177-833-801

001 Repair .

and

Repeat the inspection of the replaced Frame foot at Frame 46

on LH side, at the threshold given in the table 4 of the planning

information paragraph E.(2).

(b) Send inspection report to AIRBUS, refer to Fig. A-FRAAA.

(12) Subtask 536177-832-012-003 - Do a Detailed Inspection of the Frame Foot at FR46

on RH Side

Work Zones and Access Panels

Zone Access/Work location

148 Access Door 147BZ

Work location Frame 46

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Non Aqueous Cleaner -

General

08BAA9 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 149

5

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@A300-600

SERVICE BULLETIN

References

Drawing R53810323

Service Bulletin (SB) A300-53-6111

A300-53-6176

Fig. A-FBAAA

Inspection areas

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

Fig. A-FFLAA

Flow Chart for Frame 46 on RH side

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Fig. A-FRAAA

Inspection report

Sheet 01

Sheet 02

(a) At threshold given in the PLANNING INFORMATION Paragraph E.(2):

Do a detailed inspection of the Frame foot at Frame 46 on RH side.

Refer to Fig. A-FFLAA

Refer to Fig. A-FBAAA Sheet 01, Fig. A-FBAAA Sheet 07 and Fig. A-FBAAA Sheet

08

1 The Frame have been repaired in area 1 as per Service Bulletin No.

A300-53-6111 or R53810323:

a Clean the inspected areas with:

Non Aqueous

Cleaner - General

08BAA9 As required

b Do a detailed inspection of the area 2 of Frame foot at Frame 46 on RH

side.

<1> If crack is not found in area 2:

<a> Repeat the inspection of the Frame foot at Frame 46 on RH

side, at the interval given in the table 4 of the planning

information paragraph E.(2).

OR

<b> Apply Service Bulletin No. A300-53-6176 before next flight.

and

No further action.

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 150

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SERVICE BULLETIN

<2> If crack is found in area 2:

NOTE: If crack is higher than 30 mm (1.181 in.):

- Inform AIRBUS and send the affected Frame

foot for laboratory investigation.

- Perform the following steps.

<a> Apply Service Bulletin No. A300-53-6176 before next flight.

and

No further action.

OR

<b> Replace the cracked Frame foot at Frame 46 on RH side

before next flight, in accordance with TASK 536177-833-801

001 Repair .

and

Repeat the inspection of the replaced Frame foot at Frame 46

on RH side, at the threshold given in the table 4 of the planning

information paragraph E.(2).

(b) Send inspection report to AIRBUS, refer to Fig. A-FRAAA.

**CONF 004

None

**CONF ALL

D. TEST

**CONF 001

None

**CONF 002

None

**CONF 003

None

**CONF 004

None

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 151

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@A300-600

SERVICE BULLETIN

**CONF ALL

E. CLOSE-UP

**CONF 001

(1) Subtask 536177-942-001-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-41-53, Page Block 001

32-12-11, Page Block 301

NOTE: If you intend to accomplish an associated Repair Task during the same

layover period, the subsequent Close-up procedure is not necessary.

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) Close the access door 147BZ, refer to AMM 06-41-53, Page Block 001.

(c) Remove the access platform(s).

(d) Close the MLG door, refer to AMM 32-12-11, Page Block 301.

(e) Put the aircraft back to its initial configuration.

**CONF 002

(1) Subtask 536177-942-001-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-41-53, Page Block 001

32-12-11, Page Block 301

NOTE: If you intend to accomplish an associated Repair Task during the same

layover period, the subsequent Close-up procedure is not necessary.

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) Close the access door 147BZ, refer to AMM 06-41-53, Page Block 001.

(c) Remove the access platform(s).

(d) Close the MLG door, refer to AMM 32-12-11, Page Block 301.

(e) Put the aircraft back to its initial configuration.

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 152

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@A300-600

SERVICE BULLETIN

**CONF 003

(1) Subtask 536177-942-001-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-41-53, Page Block 001

32-12-11, Page Block 301

NOTE: If you intend to accomplish an associated Repair Task during the same

layover period, the subsequent Close-up procedure is not necessary.

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) Close the access door 147BZ, refer to AMM 06-41-53, Page Block 001.

(c) Remove the access platform(s).

(d) Close the MLG door, refer to AMM 32-12-11, Page Block 301.

(e) Put the aircraft back to its initial configuration.

**CONF 004

None

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 153

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@A300-600

SERVICE BULLETIN

This Page Intentionally Left Blank

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 154

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@A300-600

SERVICE BULLETIN

Task 536177-833-801-001 - Repair

**CONF ALL

WARNING: MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS

INCLUDED IN THE REFERENCED PROCEDURES.

WARNING: THIS PROCEDURE USES A FUEL SYSTEM ITEM THAT IS IN A CATEGORY

KNOWN AS A CRITICAL DESIGN CONFIGURATION CONTROL LIMITATION

(CDCCL). CDCCL IDENTIFIES AN ITEM THAT CAN BE THE SOURCE OF A

POSSIBLE FUEL TANK IGNITION. YOU MUST KEEP ALL CDCCL ITEMS IN

THE APPROVED CONFIGURATION. DAMAGE, WEAR OR CHANGES TO A

CDCCL ITEM CAN CAUSE A POSSIBLE FUEL TANK EXPLOSION.

MAKE SURE THAT THE GROUND SAFETY-LOCKS ARE CORRECTLY

INSTALLED ON THE LANDING GEAR. THIS PREVENTS UNWANTED

MOVEMENT OF THE LANDING GEAR.

MAKE SURE THAT YOU HAVE THE CORRECT FIRE FIGHTING EQUIPMENT

AVAILABLE.

ISOLATE ALL THE AIRCRAFT ELECTRICAL CIRCUITS. UNWANTED

ELECTRICAL POWER CAN BE DANGEROUS.

CAUTION: ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP

ELECTRICAL WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY

AND MECHANICALLY SERVICEABLE). WHEN YOU DO MAINTENANCE

WORK, REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING,

COMPONENTS AND THE WORK AREA AS CLEAN AS POSSIBLE. TO DO

THIS:

- PUT PROTECTION, SUCH AS PLASTIC SHEETING, CLOTHS, ETC, AS

NECESSARY ON WIRING AND COMPONENTS.

- REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND

OTHER CONTAMINATION.

THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION

AND DAMAGE TO THE ELECTRICAL WIRING INSTALLATION.

TheRE IS CONTAMINATION REFER TO ESPM 20-55-00.

CAUTION: DO NOT REPLACE TWO CONSECUTIVE FRAME FEET AT THE SAME TIME.

REPLACE THE FRAME FEET AT FR41 AND/OR FR43 AND/OR FR45 FIRST,

THEN REPLACE THE FRAME FEET AT FR42 AND/OR FR44 AND/OR FR46.

NOTE: The accomplishment instructions of this Service Bulletin include procedures given

in other documents or in other sections of the Service Bulletin. When the words

"refer to" are used and the operator has a procedure accepted by the local

authority he belongs to, the accepted alternative procedure can be used. When the

words "in accordance with" are used then the given procedure must be followed.

NOTE: The access and close-up instructions, not comprising return to service tests, in this

Service Bulletin do not constitute or affect the technical intent of the Service

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 155

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@A300-600

SERVICE BULLETIN

Bulletin. Operators can therefore, as deemed necessary, omit or add access and/or

close-up steps to add flexibility to their maintenance operations as long as the

technical intent of the Service Bulletin is met within the set parameters.

NOTE: Manual titles given in the accomplishment instructions are referred to by acronyms.

Refer to paragraph 1.J., References, for the definition of acronyms.

NOTE: This Service Bulletin is classified mandatory or expected to be classified mandatory

by an Airworthiness Directive (AD). The paragraphs 3.C. and 3.D. in these

accomplishment instructions are Required for Compliance (RC) and must be done

to comply with the AD. Other paragraphs are recommended and may be deviated

from, done as part of other actions or done with accepted methods different from

those given in the Service Bulletin, as long as the RC paragraphs can be done and

the aircraft can be put back into a serviceable condition.

Task Associated Data

**CONF 001

Zone

140

Manpower

TOTAL MANHOURS 541.00

ELAPSED TIME (HOURS) 42.00

**CONF 002

Zone

140

Manpower

TOTAL MANHOURS 541.00

ELAPSED TIME (HOURS) 42.00

**CONF 003

Zone

140

Manpower

TOTAL MANHOURS 541.00

ELAPSED TIME (HOURS) 42.00

**CONF 004

None

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 156

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SERVICE BULLETIN

**CONF ALL

A. GENERAL

**CONF 001

(1) Subtask 536177-910-003-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-21-00, Page Block 001

06-31-53, Page Block 001

06-41-00, Page Block 001

20-21-12, Page Block 001

20-28-11, Page Block 001

Consumable Material List (CML)

Elec. Std. Practices Manual (ESPM) 20-51-20

Structural Repair Manual (SRM) 51-24-00

51-40-00

51-40-20

51-40-30

51-40-40

(a) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001.

(b) For the identification of zones, refer to AMM 06-21-00, Page Block 001.

(c) For the identification of access panels, refer to AMM 06-41-00, Page Block 001.

(d) For the specification of materials (Mat. No.) given in this Service Bulletin, refer to

the Consumable Material List (CML).

(e) To torque tighten the standard threaded fasteners, refer to AMM 20-21-12, Page

Block 001.

(f) Remove and install fasteners in accordance with SRM 51-40-20.

(g) Apply sealant in accordance with SRM 51-24-00.

(h) Obtain fastener hole diameters and drill data in accordance with SRM 51-40-40.

(i) Obtain alternative and substitute fastener data in accordance with SRM 51-40-30.

(j) If alternative and substitute fasteners have to be used, you must make sure that the

associated nut/collar are compatible in accordance with SRM 51-40-00 "Mating

Part" column.

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 157

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SERVICE BULLETIN

(k) The length of any fastener specified in this Service Bulletin does not meet

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

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

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

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

(l) Put all the retained hardware in identified plastic bags and attach the bags to the

related unit.

(m) For the electrical bonding, refer to ESPM 20-51-20 and AMM 20-28-11, Page Block

001.

(2) Subtask 536177-839-002-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

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

Service Bulletin.

**CONF 002

(1) Subtask 536177-910-003-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-21-00, Page Block 001

06-31-53, Page Block 001

06-41-00, Page Block 001

20-21-12, Page Block 001

20-28-11, Page Block 001

Consumable Material List (CML)

Elec. Std. Practices Manual (ESPM) 20-51-20

Structural Repair Manual (SRM) 51-24-00

51-40-00

51-40-20

51-40-30

51-40-40

(a) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001.

(b) For the identification of zones, refer to AMM 06-21-00, Page Block 001.

(c) For the identification of access panels, refer to AMM 06-41-00, Page Block 001.

(d) For the specification of materials (Mat. No.) given in this Service Bulletin, refer to

the Consumable Material List (CML).

(e) To torque tighten the standard threaded fasteners, refer to AMM 20-21-12, Page

Block 001.

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 158

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@A300-600

SERVICE BULLETIN

(f) Remove and install fasteners in accordance with SRM 51-40-20.

(g) Apply sealant in accordance with SRM 51-24-00.

(h) Obtain fastener hole diameters and drill data in accordance with SRM 51-40-40.

(i) Obtain alternative and substitute fastener data in accordance with SRM 51-40-30.

(j) If alternative and substitute fasteners have to be used, you must make sure that the

associated nut/collar are compatible in accordance with SRM 51-40-00 "Mating

Part" column.

(k) The length of any fastener specified in this Service Bulletin does not meet

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

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

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

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

(l) Put all the retained hardware in identified plastic bags and attach the bags to the

related unit.

(m) For the electrical bonding, refer to ESPM 20-51-20 and AMM 20-28-11, Page Block

001.

(2) Subtask 536177-839-002-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

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

Service Bulletin.

**CONF 003

(1) Subtask 536177-910-003-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-21-00, Page Block 001

06-31-53, Page Block 001

06-41-00, Page Block 001

20-21-12, Page Block 001

20-28-11, Page Block 001

Consumable Material List (CML)

Elec. Std. Practices Manual (ESPM) 20-51-20

Structural Repair Manual (SRM) 51-24-00

51-40-00

51-40-20

51-40-30

51-40-40

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 159

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SERVICE BULLETIN

(a) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001.

(b) For the identification of zones, refer to AMM 06-21-00, Page Block 001.

(c) For the identification of access panels, refer to AMM 06-41-00, Page Block 001.

(d) For the specification of materials (Mat. No.) given in this Service Bulletin, refer to

the Consumable Material List (CML).

(e) To torque tighten the standard threaded fasteners, refer to AMM 20-21-12, Page

Block 001.

(f) Remove and install fasteners in accordance with SRM 51-40-20.

(g) Apply sealant in accordance with SRM 51-24-00.

(h) Obtain fastener hole diameters and drill data in accordance with SRM 51-40-40.

(i) Obtain alternative and substitute fastener data in accordance with SRM 51-40-30.

(j) If alternative and substitute fasteners have to be used, you must make sure that the

associated nut/collar are compatible in accordance with SRM 51-40-00 "Mating

Part" column.

(k) The length of any fastener specified in this Service Bulletin does not meet

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

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

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

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

(l) Put all the retained hardware in identified plastic bags and attach the bags to the

related unit.

(m) For the electrical bonding, refer to ESPM 20-51-20 and AMM 20-28-11, Page Block

001.

(2) Subtask 536177-839-002-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

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

Service Bulletin.

**CONF 004

None

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 160

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@A300-600

SERVICE BULLETIN

**CONF ALL

B. PREPARATION

**CONF 001

(1) Subtask 536177-941-003-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-41-53, Page Block 001

24-00-00, Page Block 301

28-00-00, Page Block 301

28-10-00, Page Block 301

28-11-29, Page Block 401

28-13-21, Page Block 401

28-25-00, Page Block 301

32-12-11, Page Block 301

WARNING: MAKE SURE THAT THE GROUND SAFETY-LOCKS ARE CORRECTLY

INSTALLED ON THE LANDING GEAR.

DO NOT CONNECT GROUND POWER OR SWITCH ON ANY

AIRCRAFT ELECTRICAL SYSTEM UNTIL THE FUEL TANKS have

been COMPLETELY DRAINED AND VENTED.

MAKE CERTAIN THAT FIRE EQUIPMENT IS AVAILABLE AND

ADEQUATE.

OBEY THE FUEL SERVICING SAFETY INSTRUCTIONS.

NOTE: If you intend to accomplish this Repair Task during the same layover

period as the associated Inspection, the subsequent Preparation

procedure is not necessary, except the defueling and the degassing of

the center tank, the openning of the access doors 147AZ and 148AZ and

the removal of the vapor seal.

NOTE: The items given in this note shall be considered as the basic Aircraft

configuration before you start a maintenance task:

- Aircraft on the ground resting on landing gear (the ground safety

locks and the wheel chocks are in position on the landing gear)

- Engine shut down, thrust reversers closed and locked

- Aircraft in clean configuration

- Parking brake applied

- Aircraft electrical network de-energized

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 161

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SERVICE BULLETIN

- Hydraulic systems depressurized

- Access to the cockpit and cabin is available

- All circuit breakers are in closed position

- All controls in NORM, AUTO or OFF position

(a) Make sure that the aircraft is electrically grounded, refer to AMM 24-00-00, Page

Block 301.

(b) Open the Main Landing Gear (MLG) door, refer to AMM 32-12-11, Page Block 301.

(c) Put an access platform in position at zone 140.

(d) Open the access door 147BZ, refer to AMM 06-41-53, Page Block 001.

(e) Defuel the center fuel tank, refer to AMM 28-25-00, Page Block 301.

(f) Degas and ventilate the center fuel tank, refer to AMM 28-00-00, Page Block 301

and refer to AMM 28-10-00, Page Block 301.

(g) Open the access doors 147AZ and 148AZ, refer to AMM 28-11-29, Page Block

401.

(h) Remove the vapor seal to get access to the Frame foot fittings to be replaced, refer

to AMM 28-13-21, Page Block 401.

**CONF 002

(1) Subtask 536177-941-003-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-41-53, Page Block 001

24-00-00, Page Block 301

28-00-00, Page Block 301

28-10-00, Page Block 301

28-11-29, Page Block 401

28-13-21, Page Block 401

28-25-00, Page Block 301

32-12-11, Page Block 301

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 162

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SERVICE BULLETIN

WARNING: MAKE SURE THAT THE GROUND SAFETY-LOCKS ARE CORRECTLY

INSTALLED ON THE LANDING GEAR.

DO NOT CONNECT GROUND POWER OR SWITCH ON ANY

AIRCRAFT ELECTRICAL SYSTEM UNTIL THE FUEL TANKS have

been COMPLETELY DRAINED AND VENTED.

MAKE CERTAIN THAT FIRE EQUIPMENT IS AVAILABLE AND

ADEQUATE.

OBEY THE FUEL SERVICING SAFETY INSTRUCTIONS.

NOTE: If you intend to accomplish this Repair Task during the same layover

period as the associated Inspection, the subsequent Preparation

procedure is not necessary, except the defueling and the degassing of

the center tank, the openning of the access doors 147AZ and 148AZ and

the removal of the vapor seal.

NOTE: The items given in this note shall be considered as the basic Aircraft

configuration before you start a maintenance task:

- Aircraft on the ground resting on landing gear (the ground safety

locks and the wheel chocks are in position on the landing gear)

- Engine shut down, thrust reversers closed and locked

- Aircraft in clean configuration

- Parking brake applied

- Aircraft electrical network de-energized

- Hydraulic systems depressurized

- Access to the cockpit and cabin is available

- All circuit breakers are in closed position

- All controls in NORM, AUTO or OFF position

(a) Make sure that the aircraft is electrically grounded, refer to AMM 24-00-00, Page

Block 301.

(b) Open the Main Landing Gear (MLG) door, refer to AMM 32-12-11, Page Block 301.

(c) Put an access platform in position at zone 140.

(d) Open the access door 147BZ, refer to AMM 06-41-53, Page Block 001.

(e) Defuel the center fuel tank, refer to AMM 28-25-00, Page Block 301.

(f) Degas and ventilate the center fuel tank, refer to AMM 28-00-00, Page Block 301

and refer to AMM 28-10-00, Page Block 301.

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 163

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@A300-600

SERVICE BULLETIN

(g) Open the access doors 147AZ and 148AZ, refer to AMM 28-11-29, Page Block

401.

(h) Remove the vapor seal to get access to the Frame foot fittings to be replaced, refer

to AMM 28-13-21, Page Block 401.

**CONF 003

(1) Subtask 536177-941-003-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-41-53, Page Block 001

24-00-00, Page Block 301

28-00-00, Page Block 301

28-10-00, Page Block 301

28-11-29, Page Block 401

28-13-21, Page Block 401

28-25-00, Page Block 301

32-12-11, Page Block 301

WARNING: MAKE SURE THAT THE GROUND SAFETY-LOCKS ARE CORRECTLY

INSTALLED ON THE LANDING GEAR.

DO NOT CONNECT GROUND POWER OR SWITCH ON ANY

AIRCRAFT ELECTRICAL SYSTEM UNTIL THE FUEL TANKS have

been COMPLETELY DRAINED AND VENTED.

MAKE CERTAIN THAT FIRE EQUIPMENT IS AVAILABLE AND

ADEQUATE.

OBEY THE FUEL SERVICING SAFETY INSTRUCTIONS.

NOTE: If you intend to accomplish this Repair Task during the same layover

period as the associated Inspection, the subsequent Preparation

procedure is not necessary, except the defueling and the degassing of

the center tank, the openning of the access doors 147AZ and 148AZ and

the removal of the vapor seal.

NOTE: The items given in this note shall be considered as the basic Aircraft

configuration before you start a maintenance task:

- Aircraft on the ground resting on landing gear (the ground safety

locks and the wheel chocks are in position on the landing gear)

- Engine shut down, thrust reversers closed and locked

- Aircraft in clean configuration

- Parking brake applied

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 164

5

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@A300-600

SERVICE BULLETIN

- Aircraft electrical network de-energized

- Hydraulic systems depressurized

- Access to the cockpit and cabin is available

- All circuit breakers are in closed position

- All controls in NORM, AUTO or OFF position

(a) Make sure that the aircraft is electrically grounded, refer to AMM 24-00-00, Page

Block 301.

(b) Open the Main Landing Gear (MLG) door, refer to AMM 32-12-11, Page Block 301.

(c) Put an access platform in position at zone 140.

(d) Open the access door 147BZ, refer to AMM 06-41-53, Page Block 001.

(e) Defuel the center fuel tank, refer to AMM 28-25-00, Page Block 301.

(f) Degas and ventilate the center fuel tank, refer to AMM 28-00-00, Page Block 301

and refer to AMM 28-10-00, Page Block 301.

(g) Open the access doors 147AZ and 148AZ, refer to AMM 28-11-29, Page Block

401.

(h) Remove the vapor seal to get access to the Frame foot fittings to be replaced, refer

to AMM 28-13-21, Page Block 401.

**CONF 004

None

**CONF ALL

C. PROCEDURE

CAUTION: DO NOT REPLACE TWO CONSECUTIVE FRAME FEET AT THE SAME

TIME. REPLACE THE FRAME FEET AT FR41 AND/OR FR43 AND/OR

FR45 FIRST, THEN REPLACE THE FRAME FEET AT FR42 AND/OR FR44

AND/OR FR46.

**CONF 001

(1) Subtask 536177-831-001-001 - Depending on Inspection results, if necessary,

remove the Fasteners from FR41, LH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 41

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 165

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@A300-600

SERVICE BULLETIN

Manpower Resources

Manhours 4.00

Minimum number of person 2

Subtask elapsed time 2.00

Skills AIRFRAME

References

Structural Repair Manual (SRM) 51-40-20

Fig. A-FVAAA

Removal/Installation of the Fasteners

from FR41 to FR46, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

(a) If necessary, to ease the replacement of the Frame foot, remove fasteners from

Frame 41, LH side.

Refer to Fig. A-FVAAA

In accordance with SRM 51-40-20

1 Remove:

20 Rivet Item (19) Discard

And:

32 Rivet Item (5) Discard

or

32 Bolt Item (3) Discard

32 Nut Item (4) Discard

(2) Subtask 536177-831-002-001 - Depending on Inspection results, remove the

Gussets from FR41, LH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 41

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills AIRFRAME

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 166

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@A300-600

SERVICE BULLETIN

References

Structural Repair Manual (SRM) 51-40-20

Fig. A-FLAAA

Removal/Installation of the Gussets at

FR41, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

(a) Remove the Gussets from Frame 41, LH side.

Refer to Fig. A-FLAAA

In accordance with SRM 51-40-20

1 Remove:

1 Gusset Item (120) Retain

1 Gusset Item (122) Retain

attached with:

4 Screw Item (3) Discard

4 Nut Item (4) Discard

(3) Subtask 536177-831-003-003 - Depending on Inspection results, remove the Frame

Foot from FR41, LH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 41

Manpower Resources

Manhours 16.00

Minimum number of person 2

Subtask elapsed time 8.00

Skills AIRFRAME

References

Structural Repair Manual (SRM) 51-40-20

Fig. A-FCAAC

Replacement of the Frame foot FR41,

LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

(a) Remove the Frame foot from Frame 41, LH side.

Refer to Fig. A-FCAAC

In accordance with SRM 51-40-20

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 167

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@A300-600

SERVICE BULLETIN

1 Remove:

1 Frame foot Item (100) Discard

1 Stiffener Item (58) Retain

1 Splice Item (60) Retain

4 Screw Item (55) Retain

4 Nut Item (56) Discard

33 Screw Item (3) Discard

33 Nut Item (4) Discard

2 Rivet Item (19) Discard

And:

11 Rivet Item (5) Discard

or

11 Rivet Item (6) Discard

11 Bush Item (7) Discard

(4) Subtask 536177-831-004-003 - Depending on Inspection results, install an identical

Frame Foot at FR41, LH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 41

Manpower Resources

Manhours 16.00

Minimum number of person 2

Subtask elapsed time 8.00

Skills AIRFRAME

Material necessary to do the job

Kit 536177A03R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

9 ASNA2529-3 36 NUT

12 ASNA2529-6 2 NUT

14 NAS1726-5E 2 NUT

16 ASNA2529-5 4 NUT

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 168

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@A300-600

SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

19 ASNA2050DXJ4020 2 RIVET

21 ASNA2529-4 2 NUT

23 EN6115V3X5 15 SCREW

24 EN6115V3X7 6 SCREW

25 EN6115V3X6 13 SCREW

26 EN6114V6X14 2 SCREW

27 ASNA2001V5-8X 2 SCREW

28 EN6114V5X8 4 SCREW

29 EN6115V3X4 2 SCREW

30 EN6114V4X8 1 SCREW

31 EN6114V4X10 1 SCREW

56 NSA5057-6 4 NUT

100 A5711112920095 1 FOOT

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant -

General Purpose Brushable

06AAA1 As required

Polysulfide Sealant - Fuel

Tank Brushable

06ABA1 As required

Polysulfide Sealant - Fuel

Tank Fillet

06ABB1 As required

References

Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001

Structural Repair Manual (SRM) 51-40-00

51-40-20

51-40-30

51-40-40

Fig. A-FCAAC

Replacement of the Frame foot FR41,

LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Fig. A-FLAAA

Removal/Installation of the Gussets at

FR41, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

(a) Install and drill all the parts.

Refer to Fig. A-FCAAC

In accordance with SRM 51-40-40

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 169

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@A300-600

SERVICE BULLETIN

1 Put all the parts in position as shown on Fig. A-FCAAC.

1 Frame foot A5711112920095 Item 100

1 Stiffener Item (58) Retained at

removal

1 Splice Item (60) Retained at

removal

NOTE: If necessary, rework the upper and side surfaces of the Frame

foot with a maximum of 0.5 mm (0.020 in.) as shown on Fig.

A-FCAAC Sheet 03.

NOTE: Between parts apply:

Polysulfide Sealant

- Fuel Tank Fillet

06ABB1 As required

2 Drill the holes of the Frame foot H1 to H23 and H26 to H31 to the diameter

given on Fig. A-FCAAC Sheet 03 and Fig. A-FCAAC Sheet 04.

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

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

(b) Install the fasteners.

Refer to Fig. A-FCAAC

In accordance with SRM 51-40-00, SRM 51-40-20 and SRM 51-40-30

Refer to AMM 20-21-12, Page Block 001

1 Install the fasteners of the Frame foot H1 to H23 and H26 to H31:

Refer to Fig. A-FCAAC Sheet 03 to Fig. A-FCAAC Sheet 05

5 Screw EN6115V3X5 Item 23

5 Screw EN6115V3X7 Item 24

13 Screw EN6115V3X6 Item 25

2 Screw ASNA2001V5-8X Item 27

4 Screw EN6114V5X8 Item 28

23 Nut ASNA2529-3 Item 9

2 Nut NAS1726-5E Item 14

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 170

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SERVICE BULLETIN

4 Nut ASNA2529-5 Item 16

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

2 Install the four upper fasteners of the Frame foot:

Refer to Fig. A-FCAAC Sheet 02

4 Screw Item (55) Retained at

removal

4 Nut NSA5057-6 Item 56

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

3 Install the fasteners of the stiffener at STGR 36 H45 and H46:

Refer to Fig. A-FCAAC Sheet 05

2 Rivet ASNA2050DXJ4020 Item 19

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

4 Install the fasteners of the splice H32 to H44:

Refer to Fig. A-FCAAC Sheet 06

10 Screw EN6115V3X5 Item 23

1 Screw EN6115V3X7 Item 24

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 171

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SERVICE BULLETIN

2 Screw EN6115V3X4 Item 29

13 Nut ASNA2529-3 Item 9

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

5 Do a sealant bead around the parts with:

Polysulfide Sealant

- Fuel Tank Fillet

06ABB1 As required

(c) Install the Gussets at Frame 41, LH side.

Refer to Fig. A-FLAAA

In accordance with SRM 51-40-20, SRM 51-40-00 and SRM 51-40-30

Refer to AMM 20-21-12, Page Block 001

1 Put the gussets in position as shown on Fig. A-FLAAA Sheet 02 and Fig. AFLAAA Sheet 03.

1 Gusset Item (120) Retained at

removal

1 Gusset Item (122) Retained at

removal

NOTE: Between the Frame foot and the aft gusset, the distance must

be 2 times the thickness of the gusset.

NOTE: Between the Frame foot and the FWD gusset, the distance

must be 1.3 times the thickness of the gusset.

2 Drill holes H24 and H25 to the diameter given on Fig. A-FLAAA Sheet 03.

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

4 Install:

1 Gusset Item (120) Retained at

removal

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 172

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@A300-600

SERVICE BULLETIN

1 Gusset Item (122) Retained at

removal

2 Screw EN6114V6X14 Item 26

1 Screw EN6114V4X8 Item 30

1 Screw EN6114V4X10 Item 31

2 Nut ASNA2529-6 Item 12

2 Nut ASNA2529-4 Item 21

(5) Subtask 536177-831-005-001 - Depending on Inspection results, if removed, install

the Fasteners at FR41, LH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 41

Manpower Resources

Manhours 6.00

Minimum number of person 2

Subtask elapsed time 3.00

Skills AIRFRAME

Material necessary to do the job

Component COMPA01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

9 ASNA2529-3 32 NUT

90 ASNA2019-56-25 32 RIVET

91 EN6114V3X5 32 SCREW

92 EN6080D6X-32 20 RIVET

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

NOTE: The components listed above are only necessary if crack is found on a

Frame foot. The quantity of these items are to be ordered as required.

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant - Fuel

Tank Brushable

06ABA1 As required

References

Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 173

5

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@A300-600

SERVICE BULLETIN

References

Structural Repair Manual (SRM) 51-24-00

51-40-00

51-40-20

51-40-30

Fig. A-FVAAA

Removal/Installation of the Fasteners

from FR41 to FR46, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

(a) If removed, install the fasteners at Frame 41, LH side.

Refer to Fig. A-FVAAA

In accordance with SRM 51-40-20, SRM 51-24-00, SRM 51-40-00 and SRM

51-40-30

Refer to AMM 20-21-12, Page Block 001

1 Install:

20 Rivet EN6080D6X-32 Item 92

And:

32 Rivet ASNA2019-56-25 Item 90

or

32 Screw EN6114V3X5 Item 91

32 Nut ASNA2529-3 Item 9

NOTE: Protect the fasteners with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

(6) Subtask 536177-831-006-001 - Depending on Inspection results, if necessary,

remove the Fasteners from FR41, RH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 41

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 174

5

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@A300-600

SERVICE BULLETIN

Manpower Resources

Manhours 4.00

Minimum number of person 2

Subtask elapsed time 2.00

Skills AIRFRAME

References

Structural Repair Manual (SRM) 51-40-20

Fig. A-FVAAA

Removal/Installation of the Fasteners

from FR41 to FR46, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

(a) If necessary, to ease the replacement of the Frame foot, remove fasteners from

Frame 41, RH side.

Refer to Fig. A-FVAAA

In accordance with SRM 51-40-20

1 Remove:

20 Rivet Item (19) Discard

And:

32 Rivet Item (5) Discard

or

32 Bolt Item (3) Discard

32 Nut Item (4) Discard

(7) Subtask 536177-831-007-001 - Depending on Inspection results, remove the

Gussets from FR41, RH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 41

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills AIRFRAME

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 175

5

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

SERVICE BULLETIN

References

Structural Repair Manual (SRM) 51-40-20

Fig. A-FLAAA

Removal/Installation of the Gussets at

FR41, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

(a) Remove the Gussets from Frame 41, RH side.

Refer to Fig. A-FLAAA

In accordance with SRM 51-40-20

1 Remove:

1 Gusset Item (121) Retain

1 Gusset Item (123) Retain

attached with:

4 Screw Item (3) Discard

4 Nut Item (4) Discard

(8) Subtask 536177-831-008-003 - Depending on Inspection results, remove the Frame

Foot from FR41, RH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 41

Manpower Resources

Manhours 16.00

Minimum number of person 2

Subtask elapsed time 8.00

Skills AIRFRAME

References

Structural Repair Manual (SRM) 51-40-20

Fig. A-FCAAC

Replacement of the Frame foot FR41,

LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

(a) Remove the Frame foot from Frame 41, RH side.

Refer to Fig. A-FCAAC

In accordance with SRM 51-40-20

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 176

5

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

SERVICE BULLETIN

1 Remove:

1 Frame foot Item (101) Discard

1 Stiffener Item (57) Retain

1 Splice Item (59) Retain

4 Screw Item (55) Retain

4 Nut Item (56) Discard

33 Screw Item (3) Discard

33 Nut Item (4) Discard

2 Rivet Item (19) Discard

And::

11 Rivet Item (5) Discard

or

11 Rivet Item (6) Discard

11 Bush Item (7) Discard

(9) Subtask 536177-831-009-003 - Depending on Inspection results, install an identical

Frame Foot at FR41, RH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 41

Manpower Resources

Manhours 16.00

Minimum number of person 2

Subtask elapsed time 8.00

Skills AIRFRAME

Material necessary to do the job

Kit 536177A21R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

9 ASNA2529-3 36 NUT

12 ASNA2529-6 2 NUT

14 NAS1726-5E 2 NUT

16 ASNA2529-5 4 NUT

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 177

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@A300-600

SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

19 ASNA2050DXJ4020 2 RIVET

21 ASNA2529-4 2 NUT

23 EN6115V3X5 15 SCREW

24 EN6115V3X7 6 SCREW

25 EN6115V3X6 13 SCREW

26 EN6114V6X14 2 SCREW

27 ASNA2001V5-8X 2 SCREW

28 EN6114V5X8 4 SCREW

29 EN6115V3X4 2 SCREW

30 EN6114V4X8 1 SCREW

31 EN6114V4X10 1 SCREW

56 NSA5057-6 4 NUT

101 A5711112920195 1 FOOT

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant -

General Purpose Brushable

06AAA1 As required

Polysulfide Sealant - Fuel

Tank Brushable

06ABA1 As required

Polysulfide Sealant - Fuel

Tank Fillet

06ABB1 As required

References

Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001

Structural Repair Manual (SRM) 51-40-00

51-40-20

51-40-30

51-40-40

Fig. A-FCAAC

Replacement of the Frame foot FR41,

LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Fig. A-FLAAA

Removal/Installation of the Gussets at

FR41, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

(a) Install and drill all the parts.

Refer to Fig. A-FCAAC

In accordance with SRM 51-40-40

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 178

5

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

SERVICE BULLETIN

1 Put all the parts in position as shown on Fig. A-FCAAC.

1 Frame foot A5711112920195 Item 101

1 Stiffener Item (57) Retained at

removal

1 Splice Item (59) Retained at

removal

NOTE: If necessary, rework the upper and side surfaces of the Frame

foot with a maximum of 0.5 mm (0.020 in.) as shown on Fig.

A-FCAAC Sheet 03.

NOTE: Between parts apply:

Polysulfide Sealant

- Fuel Tank Fillet

06ABB1 As required

2 Drill the holes of the Frame foot H1 to H23 and H26 to H31 to the diameter

given on Fig. A-FCAAC Sheet 03 and Fig. A-FCAAC Sheet 04.

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

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

(b) Install the fasteners.

Refer to Fig. A-FCAAC

In accordance with SRM 51-40-00, SRM 51-40-20 and SRM 51-40-30

Refer to AMM 20-21-12, Page Block 001

1 Install the fasteners of the Frame foot H1 to H23 and H26 to H31:

Refer to Fig. A-FCAAC Sheet 03 to Fig. A-FCAAC Sheet 05

5 Screw EN6115V3X5 Item 23

5 Screw EN6115V3X7 Item 24

13 Screw EN6115V3X6 Item 25

2 Screw ASNA2001V5-8X Item 27

4 Screw EN6114V5X8 Item 28

23 Nut ASNA2529-3 Item 9

2 Nut NAS1726-5E Item 14

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 179

5

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

SERVICE BULLETIN

4 Nut ASNA2529-5 Item 16

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

2 Install the four upper fasteners of the Frame foot:

Refer to Fig. A-FCAAC Sheet 02

4 Screw Item (55) Retained at

removal

4 Nut NSA5057-6 Item 56

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

3 Install the fasteners of the stiffener at STGR 36 H45 and H46:

Refer to Fig. A-FCAAC Sheet 05

2 Rivet ASNA2050DXJ4020 Item 19

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

4 Install the fasteners of the splice H32 to H44:

Refer to Fig. A-FCAAC Sheet 06

10 Screw EN6115V3X5 Item 23

1 Screw EN6115V3X7 Item 24

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 180

5

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

SERVICE BULLETIN

2 Screw EN6115V3X4 Item 29

13 Nut ASNA2529-3 Item 9

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

5 Do a sealant bead around the parts with:

Polysulfide Sealant

- Fuel Tank Fillet

06ABB1 As required

(c) Install the Gussets at Frame 41, LH side.

Refer to Fig. A-FLAAA

In accordance with SRM 51-40-20, SRM 51-40-00 and SRM 51-40-30

Refer to AMM 20-21-12, Page Block 001

1 Put the gussets in position as shown on Fig. A-FLAAA Sheet 02 and Fig. AFLAAA Sheet 03.

1 Gusset Item (121) Retained at

removal

1 Gusset Item (123) Retained at

removal

NOTE: Between the Frame foot and the aft gusset, the distance must

be 2 times the thickness of the gusset.

NOTE: Between the Frame foot and the FWD gusset, the distance

must be 1.3 times the thickness of the gusset.

2 Drill holes H24 and H25 to the diameter given on Fig. A-FLAAA Sheet 03.

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

4 Install:

1 Gusset Item (121) Retained at

removal

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 181

5

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

SERVICE BULLETIN

1 Gusset Item (123) Retained at

removal

2 Screw EN6114V6X14 Item 26

1 Screw EN6114V4X8 Item 30

1 Screw EN6114V4X10 Item 31

2 Nut ASNA2529-6 Item 12

2 Nut ASNA2529-4 Item 21

(10) Subtask 536177-831-010-001 - Depending on Inspection results, if removed, install

the Fasteners at FR41, RH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 41

Manpower Resources

Manhours 6.00

Minimum number of person 2

Subtask elapsed time 3.00

Skills AIRFRAME

Material necessary to do the job

Component COMPA01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

9 ASNA2529-3 32 NUT

90 ASNA2019-56-25 32 RIVET

91 EN6114V3X5 32 SCREW

92 EN6080D6X-32 20 RIVET

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

NOTE: The components listed above are only necessary if crack is found on a

Frame foot. The quantity of these items are to be ordered as required.

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant - Fuel

Tank Brushable

06ABA1 As required

References

Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 182

5

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

SERVICE BULLETIN

References

Structural Repair Manual (SRM) 51-24-00

51-40-00

51-40-20

51-40-30

Fig. A-FVAAA

Removal/Installation of the Fasteners

from FR41 to FR46, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

(a) If removed, install the fasteners at Frame 41, RH side.

Refer to Fig. A-FVAAA

In accordance with SRM 51-40-20, SRM 51-24-00, SRM 51-40-00 and SRM

51-40-30

Refer to AMM 20-21-12, Page Block 001

1 Install:

20 Rivet EN6080D6X-32 Item 92

And:

32 Rivet ASNA2019-56-25 Item 90

or

32 Screw EN6114V3X5 Item 91

32 Nut ASNA2529-3 Item 9

NOTE: Protect the fasteners with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

(11) Subtask 536177-831-011-001 - Depending on Inspection results, if necessary,

remove the Fasteners from FR42, LH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 42

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 183

5

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

SERVICE BULLETIN

Manpower Resources

Manhours 4.00

Minimum number of person 2

Subtask elapsed time 2.00

Skills AIRFRAME

References

Structural Repair Manual (SRM) 51-40-20

Fig. A-FVAAA

Removal/Installation of the Fasteners

from FR41 to FR46, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

(a) If necessary, to ease the replacement of the Frame foot, remove fasteners from

Frame 42, LH side.

Refer to Fig. A-FVAAA

In accordance with SRM 51-40-20

1 Remove:

16 Rivet Item (19) Discard

And:

24 Rivet Item (5) Discard

or

24 Bolt Item (3) Discard

24 Nut Item (4) Discard

(12) Subtask 536177-831-012-001 - Depending on Inspection results, remove the

Gussets from FR42, LH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 42

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills AIRFRAME

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 184

5

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

SERVICE BULLETIN

References

Structural Repair Manual (SRM) 51-40-20

Fig. A-FNAAA

Removal/Installation of the Gussets at

FR42, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

(a) Remove the Gussets from Frame 42, LH side.

Refer to Fig. A-FNAAA

In accordance with SRM 51-40-20

1 Remove:

1 Gusset Item (124) Retain

1 Gusset Item (126) Retain

attached with:

4 Screw Item (3) Discard

4 Nut Item (4) Discard

(13) Subtask 536177-831-013-003 - Depending on Inspection results, remove the Frame

Foot from FR42, LH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 42

Manpower Resources

Manhours 16.00

Minimum number of person 2

Subtask elapsed time 8.00

Skills AIRFRAME

References

Structural Repair Manual (SRM) 51-40-20

Fig. A-FDAAC

Replacement of the Frame foot FR42,

LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

(a) Remove the Frame foot from Frame 42, LH side.

Refer to Fig. A-FDAAC

In accordance with SRM 51-40-20

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 185

5

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

SERVICE BULLETIN

1 Remove:

1 Frame foot Item (102) Discard

1 Stiffener Item (58) Retain

1 Stiffener Item (68) Retain

1 Splice Item (66) Retain

4 Screw Item (55) Retain

4 Nut Item (56) Discard

42 Screw Item (3) Discard

42 Nut Item (4) Discard

6 Rivet Item (19) Discard

And:

16 Rivet Item (5) Discard

or

16 Rivet Item (6) Discard

16 Bush Item (7) Discard

(14) Subtask 536177-831-014-003 - Depending on Inspection results, install an identical

Frame Foot at FR42, LH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 42

Manpower Resources

Manhours 16.00

Minimum number of person 2

Subtask elapsed time 8.00

Skills AIRFRAME

Material necessary to do the job

Kit 536177A06R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

9 ASNA2529-3 48 NUT

12 ASNA2529-6 2 NUT

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 186

5

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

SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

14 NAS1726-5E 2 NUT

16 ASNA2529-5 8 NUT

19 ASNA2050DXJ4020 4 RIVET

21 ASNA2529-4 2 NUT

23 EN6115V3X5 15 SCREW

24 EN6115V3X7 5 SCREW

25 EN6115V3X6 24 SCREW

27 ASNA2001V5-8X 2 SCREW

28 EN6114V5X8 8 SCREW

29 EN6115V3X4 4 SCREW

30 EN6114V4X8 1 SCREW

31 EN6114V4X10 1 SCREW

35 EN6114V6X13 2 SCREW

56 NSA5057-6 4 NUT

102 A5711113020095 1 FOOT

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant -

General Purpose Brushable

06AAA1 As required

Polysulfide Sealant - Fuel

Tank Brushable

06ABA1 As required

Polysulfide Sealant - Fuel

Tank Fillet

06ABB1 As required

References

Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001

Structural Repair Manual (SRM) 51-40-00

51-40-20

51-40-30

51-40-40

Fig. A-FDAAC

Replacement of the Frame foot FR42,

LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Fig. A-FNAAA

Removal/Installation of the Gussets at

FR42, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

(a) Install and drill all the parts.

Fig. A-FDAAC

In accordance with SRM 51-40-40

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 187

5

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

SERVICE BULLETIN

1 Put all the parts in position as shown on Fig. A-FDAAC.

1 Frame foot A5711113020095 Item 102

1 Stiffener Item (58) Retained at

removal

1 Stiffener Item (68) Retained at

removal

1 Splice Item (66) Retained at

removal

NOTE: If necessary, rework the upper and side surfaces of the Frame

foot with a maximum of 0.5 mm (0.020 in.) as shown on Fig.

A-FDAAC Sheet 03.

NOTE: Between parts apply:

Polysulfide Sealant

- Fuel Tank Fillet

06ABB1 As required

2 Drill the holes of the Frame foot H51 to H78, H83 to H90 and H93 to H102 to

the diameter given on Fig. A-FDAAC Sheet 03 to Fig. A-FDAAC Sheet 05.

3 Drill the holes of the stiffener at STGR 36 H79 and H80 to the diameter given

on Fig. A-FDAAC Sheet 05.

NOTE: Use the existing holes of the stringers.

4 Drill the holes of the stiffener at STGR 37 H81, H82, H103 and H104 to the

diameter given on Fig. A-FDAAC Sheet 06.

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

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

(b) Install the fasteners.

Fig. A-FDAAC

In accordance with SRM 51-40-00, SRM 51-40-20 and SRM 51-40-30

Refer to AMM 20-21-12, Page Block 001

1 Install the fasteners of the Frame foot H51 to H78, H83 to H90 and H93 to

H102:

Refer to Fig. A-FDAAC Sheet 03 to Fig. A-FDAAC Sheet 05

5 Screw EN6115V3X5 Item 23

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 188

5

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

SERVICE BULLETIN

4 Screw EN6115V3X7 Item 24

24 Screw EN6115V3X6 Item 25

2 Screw ASNA2001V5-8X Item 27

8 Screw EN6114V5X8 Item 28

33 Nut ASNA2529-3 Item 9

2 Nut NAS1726-5E Item 14

8 Nut ASNA2529-5 Item 16

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

2 Install the four upper fasteners of the Frame foot:

Refer to Fig. A-FDAAC Sheet 02

4 Screw Item (55) Retained at

removal

4 Nut NSA5057-6 Item 56

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

3 Install the fasteners of the stiffeners at STGR 36 H79 and H80:

Refer to Fig. A-FDAAC Sheet 05

2 Rivet ASNA2050DXJ4020 Item 19

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 189

5

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

SERVICE BULLETIN

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

4 Install the fasteners of the stiffener at STGR 37 H81, H82, H103 and H104:

Refer to Fig. A-FDAAC Sheet 06

2 Screw EN6115V3X4 Item 29

2 Nut ASNA2529-3 Item 9

2 Rivet ASNA2050DXJ4020 Item 19

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

5 Install the fasteners of the splice H105 to H117:

Refer to Fig. A-FDAAC Sheet 06

10 Screw EN6115V3X5 Item 23

1 Screw EN6115V3X7 Item 24

2 Screw EN6115V3X4 Item 29

13 Nut ASNA2529-3 Item 9

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

6 Do a sealant bead around the parts with:

Polysulfide Sealant

- Fuel Tank Fillet

06ABB1 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 190

5

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

SERVICE BULLETIN

(c) Install the Gussets at Frame 42, LH side.

Refer to Fig. A-FNAAA

In accordance with SRM 51-40-20, SRM 51-40-00, SRM 51-40-30 and SRM

51-40-40

Refer to AMM 20-21-12, Page Block 001

1 Put the gussets in position as shown on Fig. A-FNAAA.

1 Gusset Item (124) Retained at

removal

1 Gusset Item (126) Retained at

removal

NOTE: Between the Frame foot and the aft gusset, the distance must

be 2 times the thickness of the gusset.

NOTE: Between the Frame foot and the FWD gusset, the distance

must be 1.3 times the thickness of the gusset.

2 Drill holes H91 and H92 to the diameter given on Fig. A-FNAAA Sheet 03.

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

4 Install:

1 Gusset Item (124) Retained at

removal

1 Gusset Item (126) Retained at

removal

1 Screw EN6114V4X8 Item 30

1 Screw EN6114V4X10 Item 31

2 Screw EN6114V6X13 Item 35

2 Nut ASNA2529-6 Item 12

2 Nut ASNA2529-4 Item 21

(15) Subtask 536177-831-015-001 - Depending on Inspection results, if removed, install

the Fasteners at FR42, LH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 42

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 191

5

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

SERVICE BULLETIN

Manpower Resources

Manhours 6.00

Minimum number of person 2

Subtask elapsed time 3.00

Skills AIRFRAME

Material necessary to do the job

Component COMPA02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

9 ASNA2529-3 24 NUT

90 ASNA2019-56-25 24 RIVET

91 EN6114V3X5 24 SCREW

92 EN6080D6X-32 16 RIVET

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

NOTE: The components listed above are only necessary if crack is found on a

Frame foot. The quantity of these items are to be ordered as required.

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant - Fuel

Tank Brushable

06ABA1 As required

References

Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001

Structural Repair Manual (SRM) 51-24-00

51-40-00

51-40-20

51-40-30

Fig. A-FVAAA

Removal/Installation of the Fasteners

from FR41 to FR46, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

(a) If removed, install the fasteners at Frame 42, LH side.

Refer to Fig. A-FVAAA

In accordance with SRM 51-40-20, SRM 51-24-00, SRM 51-40-00 and SRM

51-40-30

Refer to AMM 20-21-12, Page Block 001

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 192

5

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

SERVICE BULLETIN

1 Install:

16 Rivet EN6080D6X-32 Item 92

And:

24 Rivet ASNA2019-56-25 Item 90

or

24 Screw EN6114V3X5 Item 91

24 Nut ASNA2529-3 Item 9

NOTE: Protect the fasteners with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

(16) Subtask 536177-831-016-001 - Depending on Inspection results, if necessary,

remove the Fasteners from FR42, RH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 42

Manpower Resources

Manhours 4.00

Minimum number of person 2

Subtask elapsed time 2.00

Skills AIRFRAME

References

Structural Repair Manual (SRM) 51-40-20

Fig. A-FVAAA

Removal/Installation of the Fasteners

from FR41 to FR46, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

(a) If necessary, to ease the replacement of the Frame foot, remove fasteners from

Frame 42, RH side.

Refer to Fig. A-FVAAA

In accordance with SRM 51-40-20

1 Remove:

16 Rivet Item (19) Discard

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 193

5

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

SERVICE BULLETIN

And:

24 Rivet Item (5) Discard

or

24 Bolt Item (3) Discard

24 Nut Item (4) Discard

(17) Subtask 536177-831-017-001 - Depending on Inspection results, remove the

Gussets from FR42, RH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 42

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills AIRFRAME

References

Structural Repair Manual (SRM) 51-40-20

Fig. A-FNAAA

Removal/Installation of the Gussets at

FR42, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

(a) Remove the Gussets from Frame 42, RH side.

Refer to Fig. A-FNAAA

In accordance with SRM 51-40-20

1 Remove:

1 Gusset Item (125) Retain

1 Gusset Item (127) Retain

attached with:

4 Screw Item (3) Discard

4 Nut Item (4) Discard

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 194

5

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

SERVICE BULLETIN

(18) Subtask 536177-831-018-003 - Depending on Inspection results, remove the Frame

Foot from FR42, RH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 42

Manpower Resources

Manhours 16.00

Minimum number of person 2

Subtask elapsed time 8.00

Skills AIRFRAME

References

Structural Repair Manual (SRM) 51-40-20

Fig. A-FDAAC

Replacement of the Frame foot FR42,

LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

(a) Remove the Frame foot from Frame 42, RH side.

Refer to Fig. A-FDAAC

In accordance with SRM 51-40-20

1 Remove:

1 Frame foot Item (103) Discard

1 Stiffener Item (57) Retain

1 Stiffener Item (69) Retain

1 Splice Item (67) Retain

4 Screw Item (55) Retain

4 Nut Item (56) Discard

42 Screw Item (3) Discard

42 Nut Item (4) Discard

6 Rivet Item (19) Discard

And:

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 195

5

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

SERVICE BULLETIN

16 Rivet Item (5) Discard

or

16 Rivet Item (6) Discard

16 Bush Item (7) Discard

(19) Subtask 536177-831-019-003 - Depending on Inspection results, install an identical

Frame Foot at FR42, RH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 42

Manpower Resources

Manhours 16.00

Minimum number of person 2

Subtask elapsed time 8.00

Skills AIRFRAME

Material necessary to do the job

Kit 536177A24R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

9 ASNA2529-3 48 NUT

12 ASNA2529-6 2 NUT

14 NAS1726-5E 2 NUT

16 ASNA2529-5 8 NUT

19 ASNA2050DXJ4020 4 RIVET

21 ASNA2529-4 2 NUT

23 EN6115V3X15 5 SCREW

23 EN6115V3X5 10 SCREW

24 EN6115V3X7 5 SCREW

25 EN6115V3X6 24 SCREW

27 ASNA2001V5-8X 2 SCREW

28 EN6114V5X8 8 SCREW

29 EN6115V3X4 4 SCREW

30 EN6114V4X8 1 SCREW

31 EN6114V4X10 1 SCREW

35 EN6114V6X13 2 SCREW

56 NSA5057-6 4 NUT

103 A5711113020195 1 FOOT

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 196

5

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

SERVICE BULLETIN

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant -

General Purpose Brushable

06AAA1 As required

Polysulfide Sealant - Fuel

Tank Brushable

06ABA1 As required

Polysulfide Sealant - Fuel

Tank Fillet

06ABB1 As required

References

Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001

Structural Repair Manual (SRM) 51-40-00

51-40-20

51-40-30

51-40-40

Fig. A-FDAAC

Replacement of the Frame foot FR42,

LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Fig. A-FNAAA

Removal/Installation of the Gussets at

FR42, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

(a) Install and drill all the parts.

Fig. A-FDAAC

In accordance with SRM 51-40-40

1 Put all the parts in position as shown on Fig. A-FDAAC.

1 Frame foot A5711113020195 Item 103

1 Stiffener Item (57) Retained at

removal

1 Stiffener Item (69) Retained at

removal

1 Splice Item (67) Retained at

removal

NOTE: If necessary, rework the upper and side surfaces of the Frame

foot with a maximum of 0.5 mm (0.020 in.) as shown on Fig.

A-FDAAC Sheet 03.

NOTE: Between parts apply:

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 197

5

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

SERVICE BULLETIN

Polysulfide Sealant

- Fuel Tank Fillet

06ABB1 As required

2 Drill the holes of the Frame foot H51 to H78, H83 to H90 and H93 to H102 to

the diameter given on Fig. A-FDAAC Sheet 03 to Fig. A-FDAAC Sheet 05.

3 Drill the holes of the stiffener at STGR 36 H79 and H80 to the diameter given

on Fig. A-FDAAC Sheet 05.

NOTE: Use the existing holes of the stringers.

4 Drill the holes of the stiffener at STGR 37 H81, H82, H103 and H104 to the

diameter given on Fig. A-FDAAC Sheet 06.

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

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

(b) Install the fasteners.

Fig. A-FDAAC

In accordance with SRM 51-40-00, SRM 51-40-20 and SRM 51-40-30

Refer to AMM 20-21-12, Page Block 001

1 Install the fasteners of the Frame foot H51 to H78, H83 to H90 and H93 to

H102:

Refer to Fig. A-FDAAC Sheet 03 to Fig. A-FDAAC Sheet 05

5 Screw EN6115V3X15 Item 23

4 Screw EN6115V3X7 Item 24

24 Screw EN6115V3X6 Item 25

2 Screw ASNA2001V5-8X Item 27

8 Screw EN6114V5X8 Item 28

33 Nut ASNA2529-3 Item 9

2 Nut NAS1726-5E Item 14

8 Nut ASNA2529-5 Item 16

NOTE: Protect the fasteners head and nuts with:

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 198

5

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

SERVICE BULLETIN

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

2 Install the four upper fasteners of the Frame foot:

Refer to Fig. A-FDAAC Sheet 02

4 Screw Item (55) Retained at

removal

4 Nut NSA5057-6 Item 56

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

3 Install the fasteners of the stiffeners at STGR 36 H79 and H80:

Refer to Fig. A-FDAAC Sheet 05

2 Rivet ASNA2050DXJ4020 Item 19

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

4 Install the fasteners of the stiffener at STGR 37 H81, H82, H103 and H104:

Refer to Fig. A-FDAAC Sheet 06

2 Screw EN6115V3X4 Item 29

2 Nut ASNA2529-3 Item 9

2 Rivet ASNA2050DXJ4020 Item 19

NOTE: Wet install the fasteners with:

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 199

5

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

SERVICE BULLETIN

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

5 Install the fasteners of the splice H105 to H117:

Refer to Fig. A-FDAAC Sheet 06

10 Screw EN6115V3X5 Item 23

1 Screw EN6115V3X7 Item 24

2 Screw EN6115V3X4 Item 29

13 Nut ASNA2529-3 Item 9

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

6 Do a sealant bead around the parts with:

Polysulfide Sealant

- Fuel Tank Fillet

06ABB1 As required

(c) Install the Gussets at Frame 42, LH side.

Refer to Fig. A-FNAAA

In accordance with SRM 51-40-20, SRM 51-40-00, SRM 51-40-30 and SRM

51-40-40

Refer to AMM 20-21-12, Page Block 001

1 Put the gussets in position as shown on Fig. A-FNAAA.

1 Gusset Item (125) Retained at

removal

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 200

5

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

SERVICE BULLETIN

1 Gusset Item (127) Retained at

removal

NOTE: Between the Frame foot and the aft gusset, the distance must

be 2 times the thickness of the gusset.

NOTE: Between the Frame foot and the FWD gusset, the distance

must be 1.3 times the thickness of the gusset.

2 Drill holes H91 and H92 to the diameter given on Fig. A-FNAAA Sheet 03.

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

4 Install:

1 Gusset Item (125) Retained at

removal

1 Gusset Item (127) Retained at

removal

1 Screw EN6114V4X8 Item 30

1 Screw EN6114V4X10 Item 31

2 Screw EN6114V6X13 Item 35

2 Nut ASNA2529-6 Item 12

2 Nut ASNA2529-4 Item 21

(20) Subtask 536177-831-020-001 - Depending on Inspection results, if removed, install

the Fasteners at FR42, RH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 42

Manpower Resources

Manhours 6.00

Minimum number of person 2

Subtask elapsed time 3.00

Skills AIRFRAME

Material necessary to do the job

Component COMPA02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

9 ASNA2529-3 24 NUT

90 ASNA2019-56-25 24 RIVET

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 201

5

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

SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

91 EN6114V3X5 24 SCREW

92 EN6080D6X-32 16 RIVET

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

NOTE: The components listed above are only necessary if crack is found on a

Frame foot. The quantity of these items are to be ordered as required.

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant - Fuel

Tank Brushable

06ABA1 As required

References

Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001

Structural Repair Manual (SRM) 51-24-00

51-40-00

51-40-20

51-40-30

Fig. A-FVAAA

Removal/Installation of the Fasteners

from FR41 to FR46, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

(a) If removed, install the fasteners at Frame 42, RH side.

Refer to Fig. A-FVAAA

In accordance with SRM 51-40-20, SRM 51-24-00, SRM 51-40-00 and SRM

51-40-30

Refer to AMM 20-21-12, Page Block 001

1 Install:

16 Rivet EN6080D6X-32 Item 92

And:

24 Rivet ASNA2019-56-25 Item 90

or

24 Screw EN6114V3X5 Item 91

24 Nut ASNA2529-3 Item 9

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 202

5

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

SERVICE BULLETIN

NOTE: Protect the fasteners with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

(21) Subtask 536177-831-021-001 - Depending on Inspection results, if necessary,

remove the Fasteners from FR43, LH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 43

Manpower Resources

Manhours 4.00

Minimum number of person 2

Subtask elapsed time 2.00

Skills AIRFRAME

References

Structural Repair Manual (SRM) 51-40-20

Fig. A-FVAAA

Removal/Installation of the Fasteners

from FR41 to FR46, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

(a) If necessary, to ease the replacement of the Frame foot, remove fasteners from

Frame 43, LH side.

Refer to Fig. A-FVAAA

In accordance with SRM 51-40-20

1 Remove:

16 Rivet Item (19) Discard

And:

24 Rivet Item (5) Discard

or

24 Bolt Item (3) Discard

24 Nut Item (4) Discard

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 203

5

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

SERVICE BULLETIN

(22) Subtask 536177-831-022-001 - Depending on Inspection results, remove the

Gussets from FR43, LH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 43

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills AIRFRAME

References

Structural Repair Manual (SRM) 51-40-20

Fig. A-FPAAA

Removal/Installation of the Gussets at

FR43, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

(a) Remove the Gussets from Frame 43, LH side.

Refer to Fig. A-FPAAA

In accordance with SRM 51-40-20

1 Remove:

1 Gusset Item (128) Retain

1 Gusset Item (130) Retain

attached with:

4 Screw Item (3) Discard

4 Nut Item (4) Discard

(23) Subtask 536177-831-023-003 - Depending on Inspection results, remove the Frame

Foot from FR43, LH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 43

Manpower Resources

Manhours 16.00

Minimum number of person 2

Subtask elapsed time 8.00

Skills AIRFRAME

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 204

5

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

SERVICE BULLETIN

References

Structural Repair Manual (SRM) 51-40-20

Fig. A-FEAAC

Replacement of the Frame foot FR43,

LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

(a) Remove the Frame foot from Frame 43, LH side.

Refer to Fig. A-FEAAC

In accordance with SRM 51-40-20

1 Remove:

1 Frame foot Item (104) Discard

1 Stiffener Item (58) Retain

1 Splice Item (72) Retain

4 Bolt Item (55) Retain

4 Nut Item (56) Discard

34 Screw Item (3) Discard

34 Nut Item (4) Discard

2 Rivet Item (19) Discard

And:

13 Rivet Item (5) Discard

or

13 Rivet Item (6) Discard

13 Bush Item (7) Discard

(24) Subtask 536177-831-024-003 - Depending on Inspection results, install an identical

Frame Foot at FR43, LH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 43

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 205

5

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

SERVICE BULLETIN

Manpower Resources

Manhours 16.00

Minimum number of person 2

Subtask elapsed time 8.00

Skills AIRFRAME

Material necessary to do the job

Kit 536177A09R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

9 ASNA2529-3 39 NUT

12 ASNA2529-6 2 NUT

14 NAS1726-5E 2 NUT

16 ASNA2529-5 5 NUT

19 ASNA2050DXJ4020 2 RIVET

21 ASNA2529-4 1 NUT

23 EN6115V3X5 9 SCREW

24 EN6115V3X7 4 SCREW

25 EN6115V3X6 11 SCREW

26 EN6114V6X14 2 SCREW

27 ASNA2001V5-8X 2 SCREW

28 EN6114V5X8 4 SCREW

30 EN6114V4X8 1 SCREW

39 EN6115V3X9 3 SCREW

40 EN6115V3X8 11 SCREW

41 EN6114V5X10 1 SCREW

56 NSA5057-6 4 NUT

104 A5711113120095 1 FOOT

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant -

General Purpose Brushable

06AAA1 As required

Polysulfide Sealant - Fuel

Tank Brushable

06ABA1 As required

Polysulfide Sealant - Fuel

Tank Fillet

06ABB1 As required

References

Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001

Structural Repair Manual (SRM) 51-40-00

51-40-20

51-40-30

51-40-40

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 206

5

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

SERVICE BULLETIN

References

Fig. A-FEAAC

Replacement of the Frame foot FR43,

LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Fig. A-FPAAA

Removal/Installation of the Gussets at

FR43, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

(a) Install and drill all the parts.

Refer to Fig. A-FEAAC

In accordance with SRM 51-40-40

1 Put all the parts in position as shown on Fig. A-FEAAC.

1 Frame foot A5711113120095 Item 104

1 Stiffener Item (58) Retained at

removal

1 Splice Item (72) Retained at

removal

NOTE: If necessary, rework the upper and side surfaces of the Frame

foot with a maximum of 0.5 mm (0.020 in.) as shown on Fig.

A-FEAAC Sheet 03.

NOTE: Between parts apply:

Polysulfide Sealant

- Fuel Tank Fillet

06ABB1 As required

2 Drill the holes of the Frame foot H121 to H136, H140 to H149 and H152 to

H157 to the diameter given on Fig. A-FEAAC Sheet 03 to Fig. A-FEAAC

Sheet 05.

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

4 Drill the holes of the splice H137 to H139 and H158 to H167 to the diameter

given on Fig. A-FEAAC Sheet 06.

(b) Install the fasteners.

Fig. A-FEAAC

In accordance with SRM 51-40-00, SRM 51-40-20 and SRM 51-40-30

Refer to AMM 20-21-12, Page Block 001

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 207

5

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

SERVICE BULLETIN

1 Install the fasteners of the Frame foot H121 to H136, H140 to H149 and H152

to H157:

Refer to Fig. A-FEAAC Sheet 03 to Fig. A-FEAAC Sheet 05

5 Screw EN6115V3X5 Item 23

2 Screw EN6115V3X7 Item 24

11 Screw EN6115V3X6 Item 25

2 Screw ASNA2001V5-8X Item 27

4 Screw EN6114V5X8 Item 28

2 Screw EN6115V3X9 Item 39

5 Screw EN6115V3X8 Item 40

26 Nut ASNA2529-3 Item 9

2 Nut NAS1726-5E Item 14

4 Nut ASNA2529-5 Item 16

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

2 Install the four upper fasteners of the Frame foot:

Refer to Fig. A-FEAAC Sheet 04

4 Bolt Item (55) Retained at

removal

4 Nut NSA5057-6 Item 56

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 208

5

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

SERVICE BULLETIN

3 Install the fasteners of the stiffener at STGR 36 H168 and H169:

Refer to Fig. A-FEAAC Sheet 05

2 Rivet ASNA2050DXJ4020 Item 19

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

4 Install the fasteners of the splice H137 to H139 and H158 to H167:

Refer to Fig. A-FEAAC Sheet 06

4 Screw EN6115V3X5 Item 23

2 Screw EN6115V3X7 Item 24

1 Screw EN6115V3X9 Item 39

6 Screw EN6115V3X8 Item 40

13 Nut ASNA2529-3 Item 9

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

5 Do a sealant bead around the parts with:

Polysulfide Sealant

- Fuel Tank Fillet

06ABB1 As required

(c) Install the Gussets at Frame 43, LH side.

Refer to Fig. A-FPAAA

In accordance with SRM 51-40-20, SRM 51-40-00, SRM 51-40-30 and SRM

51-40-40

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 209

5

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

SERVICE BULLETIN

Refer to AMM 20-21-12, Page Block 001

1 Put the gussets in position as shown on Fig. A-FPAAA Sheet 02 and Fig. AFPAAA Sheet 03.

1 Gusset Item (128) Retained at

removal

1 Gusset Item (130) Retained at

removal

NOTE: Between the Frame foot and the aft gusset, the distance must

be 2 times the thickness of the gusset.

NOTE: Between the Frame foot and the FWD gusset, the distance

must be 1.3 times the thickness of the gusset.

2 Drill holes H150 and H151 to the diameter given on Fig. A-FPAAA Sheet 03.

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

4 Install:

1 Gusset Item (128) Retained at

removal

1 Gusset Item (130) Retained at

removal

2 Screw EN6114V6X14 Item 26

1 Screw EN6114V4X8 Item 30

1 Screw EN6114V5X10 Item 41

2 Nut ASNA2529-6 Item 12

1 Nut ASNA2529-5 Item 16

1 Nut ASNA2529-4 Item 21

(25) Subtask 536177-831-025-001 - Depending on Inspection results, if removed, install

the Fasteners at FR43, LH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 43

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 210

5

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

SERVICE BULLETIN

Manpower Resources

Manhours 6.00

Minimum number of person 2

Subtask elapsed time 3.00

Skills AIRFRAME

Material necessary to do the job

Component COMPA03

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

9 ASNA2529-3 24 NUT

47 EN6114V3X6 24 SCREW

90 ASNA2019-56-25 24 RIVET

92 EN6080D6X-32 16 RIVET

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

NOTE: The components listed above are only necessary if crack is found on a

Frame foot. The quantity of these items are to be ordered as required.

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant - Fuel

Tank Brushable

06ABA1 As required

References

Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001

Structural Repair Manual (SRM) 51-24-00

51-40-00

51-40-20

51-40-30

Fig. A-FVAAA

Removal/Installation of the Fasteners

from FR41 to FR46, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

(a) If removed, install the fasteners at Frame 43, LH side.

Refer to Fig. A-FVAAA

In accordance with SRM 51-40-20, SRM 51-24-00, SRM 51-40-00 and SRM

51-40-30

Refer to AMM 20-21-12, Page Block 001

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 211

5

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

SERVICE BULLETIN

1 Install:

16 Rivet EN6080D6X-32 Item 92

And:

24 Rivet ASNA2019-56-25 Item 90

or

24 Screw EN6114V3X6 Item 47

24 Nut ASNA2529-3 Item 9

NOTE: Protect the fasteners with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

(26) Subtask 536177-831-026-001 - Depending on Inspection results, if necessary,

remove the Fasteners from FR43, RH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 43

Manpower Resources

Manhours 4.00

Minimum number of person 2

Subtask elapsed time 2.00

Skills AIRFRAME

References

Structural Repair Manual (SRM) 51-40-20

Fig. A-FVAAA

Removal/Installation of the Fasteners

from FR41 to FR46, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

(a) If necessary, to ease the replacement of the Frame foot, remove fasteners from

Frame 43, RH side.

Refer to Fig. A-FVAAA

In accordance with SRM 51-40-20

1 Remove:

16 Rivet Item (19) Discard

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 212

5

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

SERVICE BULLETIN

And:

24 Rivet Item (5) Discard

or

24 Bolt Item (3) Discard

24 Nut Item (4) Discard

(27) Subtask 536177-831-027-001 - Depending on Inspection results, remove the

Gussets from FR43, RH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 43

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills AIRFRAME

References

Structural Repair Manual (SRM) 51-40-20

Fig. A-FPAAA

Removal/Installation of the Gussets at

FR43, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

(a) Remove the Gussets from Frame 43, RH side.

Refer to Fig. A-FPAAA

In accordance with SRM 51-40-20

1 Remove:

1 Gusset Item (129) Retain

1 Gusset Item (131) Retain

attached with:

4 Screw Item (3) Discard

4 Nut Item (4) Discard

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 213

5

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

SERVICE BULLETIN

(28) Subtask 536177-831-028-003 - Depending on Inspection results, remove the Frame

Foot from FR43, RH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 43

Manpower Resources

Manhours 16.00

Minimum number of person 2

Subtask elapsed time 8.00

Skills AIRFRAME

References

Structural Repair Manual (SRM) 51-40-20

Fig. A-FEAAC

Replacement of the Frame foot FR43,

LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

(a) Remove the Frame foot from Frame 43, RH side.

Refer to Fig. A-FEAAC

In accordance with SRM 51-40-20

1 Remove:

1 Frame foot Item (105) Discard

1 Stiffener Item (57) Retain

1 Splice Item (71) Retain

4 Bolt Item (55) Retain

4 Nut Item (56) Discard

34 Screw Item (3) Discard

34 Nut Item (4) Discard

2 Rivet Item (19) Discard

And:

13 Rivet Item (5) Discard

or

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 214

5

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

SERVICE BULLETIN

13 Rivet Item (6) Discard

13 Bush Item (7) Discard

(29) Subtask 536177-831-029-003 - Depending on Inspection results, install an identical

Frame Foot at FR43, RH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 43

Manpower Resources

Manhours 16.00

Minimum number of person 2

Subtask elapsed time 8.00

Skills AIRFRAME

Material necessary to do the job

Kit 536177A27R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

9 ASNA2529-3 39 NUT

12 ASNA2529-6 2 NUT

14 NAS1726-5E 2 NUT

16 ASNA2529-5 5 NUT

19 ASNA2050DXJ4020 2 RIVET

21 ASNA2529-4 1 NUT

23 EN6115V3X5 9 SCREW

24 EN6115V3X7 4 SCREW

25 EN6115V3X6 11 SCREW

26 EN6114V6X14 2 SCREW

27 ASNA2001V5-8X 2 SCREW

28 EN6114V5X8 4 SCREW

30 EN6114V4X8 1 SCREW

39 EN6115V3X9 3 SCREW

40 EN6115V3X8 11 SCREW

41 EN6114V5X10 1 SCREW

56 NSA5057-6 4 NUT

105 A5711113120195 1 FOOT

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant -

General Purpose Brushable

06AAA1 As required

Polysulfide Sealant - Fuel

Tank Brushable

06ABA1 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 215

5

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

SERVICE BULLETIN

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant - Fuel

Tank Fillet

06ABB1 As required

References

Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001

Structural Repair Manual (SRM) 51-40-00

51-40-20

51-40-30

51-40-40

Fig. A-FEAAC

Replacement of the Frame foot FR43,

LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Fig. A-FPAAA

Removal/Installation of the Gussets at

FR43, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

(a) Install and drill all the parts.

Refer to Fig. A-FEAAC

In accordance with SRM 51-40-40

1 Put all the parts in position as shown on Fig. A-FEAAC.

1 Frame foot A5711113120195 Item 105

1 Stiffener Item (57) Retained at

removal

1 Splice Item (71) Retained at

removal

NOTE: If necessary, rework the upper and side surfaces of the Frame

foot with a maximum of 0.5 mm (0.020 in.) as shown on Fig.

A-FEAAC Sheet 03.

NOTE: Between parts apply:

Polysulfide Sealant

- Fuel Tank Fillet

06ABB1 As required

2 Drill the holes of the Frame foot H121 to H136, H140 to H149 and H152 to

H157 to the diameter given on Fig. A-FEAAC Sheet 03 to Fig. A-FEAAC

Sheet 05.

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

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 216

5

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

SERVICE BULLETIN

4 Drill the holes of the splice H137 to H139 and H158 to H167 to the diameter

given on Fig. A-FEAAC Sheet 06.

(b) Install the fasteners.

Fig. A-FEAAC

In accordance with SRM 51-40-00, SRM 51-40-20 and SRM 51-40-30

Refer to AMM 20-21-12, Page Block 001

1 Install the fasteners of the Frame foot H121 to H136, H140 to H149 and H152

to H157:

Refer to Fig. A-FEAAC Sheet 03 to Fig. A-FEAAC Sheet 05

5 Screw EN6115V3X5 Item 23

2 Screw EN6115V3X7 Item 24

11 Screw EN6115V3X6 Item 25

2 Screw ASNA2001V5-8X Item 27

4 Screw EN6114V5X8 Item 28

2 Screw EN6115V3X9 Item 39

5 Screw EN6115V3X8 Item 40

26 Nut ASNA2529-3 Item 9

2 Nut NAS1726-5E Item 14

4 Nut ASNA2529-5 Item 16

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

2 Install the four upper fasteners of the Frame foot:

Refer to Fig. A-FEAAC Sheet 04

4 Bolt Item (55) Retained at

removal

4 Nut NSA5057-6 Item 56

NOTE: Wet install the fasteners with:

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 217

5

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

SERVICE BULLETIN

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

3 Install the fasteners of the stiffener at STGR 36 H168 and H169:

Refer to Fig. A-FEAAC Sheet 05

2 Rivet ASNA2050DXJ4020 Item 19

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

4 Install the fasteners of the splice H137 to H139 and H158 to H167:

Refer to Fig. A-FEAAC Sheet 06

4 Screw EN6115V3X5 Item 23

2 Screw EN6115V3X7 Item 24

1 Screw EN6115V3X9 Item 39

6 Screw EN6115V3X8 Item 40

13 Nut ASNA2529-3 Item 9

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 218

5

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

SERVICE BULLETIN

5 Do a sealant bead around the parts with:

Polysulfide Sealant

- Fuel Tank Fillet

06ABB1 As required

(c) Install the Gussets at Frame 43, LH side.

Refer to Fig. A-FPAAA

In accordance with SRM 51-40-20, SRM 51-40-00, SRM 51-40-30 and SRM

51-40-40

Refer to AMM 20-21-12, Page Block 001

1 Put the gussets in position as shown on Fig. A-FPAAA Sheet 02 and Fig. AFPAAA Sheet 03.

1 Gusset Item (129) Retained at

removal

1 Gusset Item (131) Retained at

removal

NOTE: Between the Frame foot and the aft gusset, the distance must

be 2 times the thickness of the gusset.

NOTE: Between the Frame foot and the FWD gusset, the distance

must be 1.3 times the thickness of the gusset.

2 Drill holes H150 and H151 to the diameter given on Fig. A-FPAAA Sheet 03.

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

4 Install:

1 Gusset Item (129) Retained at

removal

1 Gusset Item (131) Retained at

removal

2 Screw EN6114V6X14 Item 26

1 Screw EN6114V4X8 Item 30

1 Screw EN6114V5X10 Item 41

2 Nut ASNA2529-6 Item 12

1 Nut ASNA2529-5 Item 16

1 Nut ASNA2529-4 Item 21

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 219

5

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

SERVICE BULLETIN

(30) Subtask 536177-831-030-001 - Depending on Inspection results, if removed, install

the Fasteners at FR43, RH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 43

Manpower Resources

Manhours 6.00

Minimum number of person 2

Subtask elapsed time 3.00

Skills AIRFRAME

Material necessary to do the job

Component COMPA03

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

9 ASNA2529-3 24 NUT

47 EN6114V3X6 24 SCREW

90 ASNA2019-56-25 24 RIVET

92 EN6080D6X-32 16 RIVET

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

NOTE: The components listed above are only necessary if crack is found on a

Frame foot. The quantity of these items are to be ordered as required.

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant - Fuel

Tank Brushable

06ABA1 As required

References

Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001

Structural Repair Manual (SRM) 51-24-00

51-40-00

51-40-20

51-40-30

Fig. A-FVAAA

Removal/Installation of the Fasteners

from FR41 to FR46, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 220

5

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

SERVICE BULLETIN

(a) If removed, install the fasteners at Frame 43, RH side.

Refer to Fig. A-FVAAA

In accordance with SRM 51-40-20, SRM 51-24-00, SRM 51-40-00 and SRM

51-40-30

Refer to AMM 20-21-12, Page Block 001

1 Install:

16 Rivet EN6080D6X-32 Item 92

And:

24 Rivet ASNA2019-56-25 Item 90

or

24 Screw EN6114V3X6 Item 47

24 Nut ASNA2529-3 Item 9

NOTE: Protect the fasteners with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

(31) Subtask 536177-831-031-001 - Depending on Inspection results, if necessary,

remove the Fasteners from FR44, LH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 44

Manpower Resources

Manhours 4.00

Minimum number of person 2

Subtask elapsed time 2.00

Skills AIRFRAME

References

Structural Repair Manual (SRM) 51-40-20

Fig. A-FVAAA

Removal/Installation of the Fasteners

from FR41 to FR46, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 221

5

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

SERVICE BULLETIN

(a) If necessary, to ease the replacement of the Frame foot, remove fasteners from

Frame 44, LH side.

Refer to Fig. A-FVAAA

In accordance with SRM 51-40-20

1 Remove:

16 Rivet Item (19) Discard

And:

24 Rivet Item (5) Discard

or

24 Bolt Item (3) Discard

24 Nut Item (4) Discard

(32) Subtask 536177-831-032-001 - Depending on Inspection results, remove the

Gussets from FR44, LH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 44

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills AIRFRAME

References

Structural Repair Manual (SRM) 51-40-20

Fig. A-FQAAA

Removal/Installation of the Gussets at

FR44, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

(a) Remove the Gussets from Frame 44, LH side.

Refer to Fig. A-FQAAA

In accordance with SRM 51-40-20

1 Remove:

1 Gusset Item (132) Retain

1 Gusset Item (134) Retain

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 222

5

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

SERVICE BULLETIN

attached with:

4 Screw Item (3) Discard

4 Nut Item (4) Discard

(33) Subtask 536177-831-033-003 - Depending on Inspection results, remove the Frame

Foot from FR44, LH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 44

Manpower Resources

Manhours 16.00

Minimum number of person 2

Subtask elapsed time 8.00

Skills AIRFRAME

References

Structural Repair Manual (SRM) 51-40-20

Fig. A-FGAAC

Replacement of the Frame foot FR44,

LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

(a) Remove the Frame foot from Frame 44, LH side.

Refer to Fig. A-FGAAC

In accordance with SRM 51-40-20

1 Remove:

1 Frame foot Item (106) Discard

1 Stiffener Item (58) Retain

1 Splice Item (74) Retain

4 Bolt Item (55) Retain

4 Nut Item (56) Discard

29 Screw Item (3) Discard

29 Nut Item (4) Discard

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 223

5

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

SERVICE BULLETIN

2 Rivet Item (19) Discard

And:

12 Rivet Item (5) Discard

or

12 Rivet Item (6) Discard

12 Bush Item (7) Discard

(34) Subtask 536177-831-034-003 - Depending on Inspection results, install an identical

Frame Foot at FR44, LH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 44

Manpower Resources

Manhours 16.00

Minimum number of person 2

Subtask elapsed time 8.00

Skills AIRFRAME

Material necessary to do the job

Kit 536177A12R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

9 ASNA2529-3 35 NUT

12 ASNA2529-6 2 NUT

14 NAS1726-5E 2 NUT

16 ASNA2529-5 4 NUT

19 ASNA2050DXJ4020 2 RIVET

23 EN6115V3X5 10 SCREW

24 EN6115V3X7 11 SCREW

25 EN6115V3X6 12 SCREW

26 EN6114V6X14 2 SCREW

27 ASNA2001V5-8X 2 SCREW

28 EN6114V5X8 3 SCREW

29 EN6115V3X4 2 SCREW

41 EN6114V5X10 1 SCREW

56 NSA5057-6 4 NUT

106 A5711113220095 1 FOOT

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 224

5

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

SERVICE BULLETIN

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant -

General Purpose Brushable

06AAA1 As required

Polysulfide Sealant - Fuel

Tank Brushable

06ABA1 As required

Polysulfide Sealant - Fuel

Tank Fillet

06ABB1 As required

References

Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001

Structural Repair Manual (SRM) 51-40-00

51-40-20

51-40-30

51-40-40

Fig. A-FQAAA

Removal/Installation of the Gussets at

FR44, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Fig. A-FGAAC

Replacement of the Frame foot FR44,

LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

(a) Install and drill all the parts.

Refer to Fig. A-FGAAC

In accordance with SRM 51-40-40

1 Put all the parts in position as shown on Fig. A-FGAAC.

1 Frame foot A5711113220095 Item 106

1 Stiffener Item (58) Retained at

removal

1 Splice Item (74) Retained at

removal

NOTE: If necessary, rework the upper and side surfaces of the Frame

foot with a maximum of 0.5 mm (0.020 in.) as shown on Fig.

A-FGAAC Sheet 03.

NOTE: Between parts apply:

Polysulfide Sealant

- Fuel Tank Fillet

06ABB1 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 225

5

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

SERVICE BULLETIN

2 Drill the holes of the Frame foot H180 to H202 and H205 to H208 to the

diameter given on Fig. A-FGAAC Sheet 03 to Fig. A-FGAAC Sheet 05.

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

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

(b) Install the fasteners.

Refer to Fig. A-FGAAC

In accordance with SRM 51-40-00, SRM 51-40-20 and SRM 51-40-30

Refer to AMM 20-21-12, Page Block 001

1 Install the fasteners of the Frame foot H180 to H202 and H205 to H208:

Refer to Fig. A-FGAAC Sheet 03 to Fig. A-FGAAC Sheet 05

1 Screw EN6115V3X5 Item 23

10 Screw EN6115V3X7 Item 24

12 Screw EN6115V3X6 Item 25

2 Screw ASNA2001V5-8X Item 27

2 Screw EN6114V5X8 Item 28

23 Nut ASNA2529-3 Item 9

2 Nut NAS1726-5E Item 14

2 Nut ASNA2529-5 Item 16

NOTE: For holes H205 to H208, adjust the shims as shown on Fig. AFGAAC Sheet 05.

NOTE: Wet install the fasteners except for holes H203 and H204 with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 226

5

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

SERVICE BULLETIN

2 Install the four upper fasteners of the Frame foot:

Refer to Fig. A-FGAAC Sheet 02

4 Bolt Item (55) Retained at

removal

4 Nut NSA5057-6 Item 56

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

3 Install the fasteners of the stiffener at STGR 36 H221 and H222:

Refer to Fig. A-FGAAC Sheet 03

2 Rivet ASNA2050DXJ4020 Item 19

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

4 Install the fasteners of the splice H209 to H220:

Refer to Fig. A-FGAAC Sheet 06

1 Screw EN6115V3X7 Item 24

9 Screw EN6115V3X5 Item 23

2 Screw EN6115V3X4 Item 29

12 Nut ASNA2529-3 Item 9

NOTE: Wet install the fasteners with:

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 227

5

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

SERVICE BULLETIN

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

5 Do a sealant bead around the parts with:

Polysulfide Sealant

- Fuel Tank Fillet

06ABB1 As required

(c) Install the Gussets at Frame 44, LH side.

Refer to Fig. A-FQAAA

In accordance with SRM 51-40-20, SRM 51-40-00 and SRM 51-40-30

Refer to AMM 20-21-12, Page Block 001

1 Put the gussets in position as shown on Fig. A-FQAAA.

1 Gusset Item (132) Retained at

removal

1 Gusset Item (134) Retained at

removal

NOTE: Between the Frame foot and the aft gusset, the distance must

be 2 times the thickness of the gusset.

NOTE: Between the Frame foot and the FWD gusset, the distance

must be 1.3 times the thickness of the gusset.

2 Drill holes H203 and H204 to the diameter given on Fig. A-FQAAA Sheet 03.

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

4 Install:

1 Gusset Item (132) Retained at

removal

1 Gusset Item (134) Retained at

removal

2 Screw EN6114V6X14 Item 26

1 Screw EN6114V5X8 Item 28

1 Screw EN6114V5X10 Item 41

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 228

5

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

SERVICE BULLETIN

2 Nut ASNA2529-6 Item 12

2 Nut ASNA2529-5 Item 16

(35) Subtask 536177-831-035-001 - Depending on Inspection results, if removed, install

the Fasteners at FR44, LH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 44

Manpower Resources

Manhours 6.00

Minimum number of person 2

Subtask elapsed time 3.00

Skills AIRFRAME

Material necessary to do the job

Component COMPA02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

9 ASNA2529-3 24 NUT

90 ASNA2019-56-25 24 RIVET

91 EN6114V3X5 24 SCREW

92 EN6080D6X-32 16 RIVET

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

NOTE: The components listed above are only necessary if crack is found on a

Frame foot. The quantity of these items are to be ordered as required.

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant - Fuel

Tank Brushable

06ABA1 As required

References

Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001

Structural Repair Manual (SRM) 51-24-00

51-40-00

51-40-20

51-40-30

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 229

5

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

SERVICE BULLETIN

References

Fig. A-FVAAA

Removal/Installation of the Fasteners

from FR41 to FR46, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

(a) If removed, install the fasteners at Frame 44, LH side.

Refer to Fig. A-FVAAA

In accordance with SRM 51-40-20, SRM 51-24-00, SRM 51-40-00 and SRM

51-40-30

Refer to AMM 20-21-12, Page Block 001

1 Install:

16 Rivet EN6080D6X-32 Item 92

And:

24 Rivet ASNA2019-56-25 Item 90

or

24 Screw EN6114V3X5 Item 91

24 Nut ASNA2529-3 Item 9

NOTE: Protect the fasteners with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

(36) Subtask 536177-831-036-001 - Depending on Inspection results, if necessary,

remove the Fasteners from FR44, RH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 44

Manpower Resources

Manhours 4.00

Minimum number of person 2

Subtask elapsed time 2.00

Skills AIRFRAME

References

Structural Repair Manual (SRM) 51-40-20

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 230

5

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@A300-600

SERVICE BULLETIN

References

Fig. A-FVAAA

Removal/Installation of the Fasteners

from FR41 to FR46, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

(a) If necessary, to ease the replacement of the Frame foot, remove fasteners from

Frame 44, RH side.

Refer to Fig. A-FVAAA

In accordance with SRM 51-40-20

1 Remove:

16 Rivet Item (19) Discard

And:

24 Rivet Item (5) Discard

or

24 Bolt Item (3) Discard

24 Nut Item (4) Discard

(37) Subtask 536177-831-037-001 - Depending on Inspection results, remove the

Gussets from FR44, RH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 44

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills AIRFRAME

References

Structural Repair Manual (SRM) 51-40-20

Fig. A-FQAAA

Removal/Installation of the Gussets at

FR44, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

(a) Remove the Gussets from Frame 44, RH side.

Refer to Fig. A-FQAAA

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 231

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@A300-600

SERVICE BULLETIN

In accordance with SRM 51-40-20

1 Remove:

1 Gusset Item (133) Retain

1 Gusset Item (135) Retain

attached with:

4 Screw Item (3) Discard

4 Nut Item (4) Discard

(38) Subtask 536177-831-038-003 - Depending on Inspection results, remove the Frame

Foot from FR44, RH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 44

Manpower Resources

Manhours 16.00

Minimum number of person 2

Subtask elapsed time 8.00

Skills AIRFRAME

References

Structural Repair Manual (SRM) 51-40-20

Fig. A-FGAAC

Replacement of the Frame foot FR44,

LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

(a) Remove the Frame foot from Frame 44, RH side.

Refer to Fig. A-FGAAC

In accordance with SRM 51-40-20

1 Remove:

1 Frame foot Item (107) Discard

1 Stiffener Item (57) Retain

1 Splice Item (75) Retain

4 Bolt Item (55) Retain

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 232

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@A300-600

SERVICE BULLETIN

4 Nut Item (56) Discard

29 Screw Item (3) Discard

29 Nut Item (4) Discard

2 Rivet Item (19) Discard

And:

12 Rivet Item (5) Discard

or

12 Rivet Item (6) Discard

12 Bush Item (7) Discard

(39) Subtask 536177-831-039-003 - Depending on Inspection results, install an identical

Frame Foot at FR44, RH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 44

Manpower Resources

Manhours 16.00

Minimum number of person 2

Subtask elapsed time 8.00

Skills AIRFRAME

Material necessary to do the job

Kit 536177A30R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

9 ASNA2529-3 35 NUT

12 ASNA2529-6 2 NUT

14 NAS1726-5E 2 NUT

16 ASNA2529-5 4 NUT

19 ASNA2050DXJ4020 2 RIVET

23 EN6115V3X5 10 SCREW

24 EN6115V3X7 11 SCREW

25 EN6115V3X6 12 SCREW

26 EN6114V6X14 2 SCREW

27 ASNA2001V5-8X 2 SCREW

28 EN6114V5X8 3 SCREW

29 EN6115V3X4 2 SCREW

41 EN6114V5X10 1 SCREW

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 233

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@A300-600

SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

56 NSA5057-6 4 NUT

107 A5711113220195 1 FOOT

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant -

General Purpose Brushable

06AAA1 As required

Polysulfide Sealant - Fuel

Tank Brushable

06ABA1 As required

Polysulfide Sealant - Fuel

Tank Fillet

06ABB1 As required

References

Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001

Structural Repair Manual (SRM) 51-40-00

51-40-20

51-40-30

51-40-40

Fig. A-FGAAC

Replacement of the Frame foot FR44,

LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Fig. A-FQAAA

Removal/Installation of the Gussets at

FR44, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

(a) Install and drill all the parts.

Refer to Fig. A-FGAAC

In accordance with SRM 51-40-40

1 Put all the parts in position as shown on Fig. A-FGAAC.

1 Frame foot A5711113220195 Item 107

1 Stiffener Item (57) Retained at

removal

1 Splice Item (75) Retained at

removal

NOTE: If necessary, rework the upper and side surfaces of the Frame

foot with a maximum of 0.5 mm (0.020 in.) as shown on Fig.

A-FGAAC Sheet 03.

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 234

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@A300-600

SERVICE BULLETIN

NOTE: Between parts apply:

Polysulfide Sealant

- Fuel Tank Fillet

06ABB1 As required

2 Drill the holes of the Frame foot H180 to H202 and H205 to H208 to the

diameter given on Fig. A-FGAAC Sheet 03 to Fig. A-FGAAC Sheet 05.

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

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

(b) Install the fasteners.

Refer to Fig. A-FGAAC

In accordance with SRM 51-40-00, SRM 51-40-20 and SRM 51-40-30

Refer to AMM 20-21-12, Page Block 001

1 Install the fasteners of the Frame foot H180 to H202 and H205 to H208:

Refer to Fig. A-FGAAC Sheet 03 to Fig. A-FGAAC Sheet 05

1 Screw EN6115V3X5 Item 23

10 Screw EN6115V3X7 Item 24

12 Screw EN6115V3X6 Item 25

2 Screw ASNA2001V5-8X Item 27

2 Screw EN6114V5X8 Item 28

23 Nut ASNA2529-3 Item 9

2 Nut NAS1726-5E Item 14

2 Nut ASNA2529-5 Item 16

NOTE: For holes H205 to H208, adjust the shims as shown on Fig. AFGAAC Sheet 05.

NOTE: Wet install the fasteners except for holes H203 and H204 with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 235

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@A300-600

SERVICE BULLETIN

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

2 Install the four upper fasteners of the Frame foot:

Refer to Fig. A-FGAAC Sheet 02

4 Bolt Item (55) Retained at

removal

4 Nut NSA5057-6 Item 56

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

3 Install the fasteners of the stiffener at STGR 36 H221 and H222:

Refer to Fig. A-FGAAC Sheet 03

2 Rivet ASNA2050DXJ4020 Item 19

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

4 Install the fasteners of the splice H209 to H220:

Refer to Fig. A-FGAAC Sheet 06

1 Screw EN6115V3X7 Item 24

9 Screw EN6115V3X5 Item 23

2 Screw EN6115V3X4 Item 29

12 Nut ASNA2529-3 Item 9

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 236

5

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

SERVICE BULLETIN

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

5 Do a sealant bead around the parts with:

Polysulfide Sealant

- Fuel Tank Fillet

06ABB1 As required

(c) Install the Gussets at Frame 44, LH side.

Refer to Fig. A-FQAAA

In accordance with SRM 51-40-20, SRM 51-40-00 and SRM 51-40-30

Refer to AMM 20-21-12, Page Block 001

1 Put the gussets in position as shown on Fig. A-FQAAA.

1 Gusset Item (133) Retained at

removal

1 Gusset Item (135) Retained at

removal

NOTE: Between the Frame foot and the aft gusset, the distance must

be 2 times the thickness of the gusset.

NOTE: Between the Frame foot and the FWD gusset, the distance

must be 1.3 times the thickness of the gusset.

2 Drill holes H203 and H204 to the diameter given on Fig. A-FQAAA Sheet 03.

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

4 Install:

1 Gusset Item (133) Retained at

removal

1 Gusset Item (135) Retained at

removal

2 Screw EN6114V6X14 Item 26

1 Screw EN6114V5X8 Item 28

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 237

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

SERVICE BULLETIN

1 Screw EN6114V5X10 Item 41

2 Nut ASNA2529-6 Item 12

2 Nut ASNA2529-5 Item 16

(40) Subtask 536177-831-040-001 - Depending on Inspection results, if removed, install

the Fasteners at FR44, RH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 44

Manpower Resources

Manhours 6.00

Minimum number of person 2

Subtask elapsed time 3.00

Skills AIRFRAME

Material necessary to do the job

Component COMPA02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

9 ASNA2529-3 24 NUT

90 ASNA2019-56-25 24 RIVET

91 EN6114V3X5 24 SCREW

92 EN6080D6X-32 16 RIVET

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

NOTE: The components listed above are only necessary if crack is found on a

Frame foot. The quantity of these items are to be ordered as required.

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant - Fuel

Tank Brushable

06ABA1 As required

References

Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001

Structural Repair Manual (SRM) 51-24-00

51-40-00

51-40-20

51-40-30

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 238

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

SERVICE BULLETIN

References

Fig. A-FVAAA

Removal/Installation of the Fasteners

from FR41 to FR46, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

(a) If removed, install the fasteners at Frame 44, RH side.

Refer to Fig. A-FVAAA

In accordance with SRM 51-40-20, SRM 51-24-00, SRM 51-40-00 and SRM

51-40-30

Refer to AMM 20-21-12, Page Block 001

1 Install:

16 Rivet EN6080D6X-32 Item 92

And:

24 Rivet ASNA2019-56-25 Item 90

or

24 Screw EN6114V3X5 Item 91

24 Nut ASNA2529-3 Item 9

NOTE: Protect the fasteners with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

(41) Subtask 536177-831-041-001 - Depending on Inspection results, if necessary,

remove the Fasteners from FR45, LH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 45

Manpower Resources

Manhours 4.00

Minimum number of person 2

Subtask elapsed time 2.00

Skills AIRFRAME

References

Structural Repair Manual (SRM) 51-40-20

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 239

5

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

SERVICE BULLETIN

References

Fig. A-FVAAA

Removal/Installation of the Fasteners

from FR41 to FR46, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

(a) If necessary, to ease the replacement of the Frame foot, remove fasteners from

Frame 45, LH side.

Refer to Fig. A-FVAAA

In accordance with SRM 51-40-20

1 Remove:

20 Rivet Item (19) Discard

And:

32 Rivet Item (5) Discard

or

32 Bolt Item (3) Discard

32 Nut Item (4) Discard

(42) Subtask 536177-831-042-001 - Depending on Inspection results, remove the

Gussets from FR45, LH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 45

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills AIRFRAME

References

Structural Repair Manual (SRM) 51-40-20

Fig. A-FTAAA

Removal/Installation of the Gussets at

FR45, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

(a) Remove the Gussets from Frame 45, LH side.

Refer to Fig. A-FTAAA

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 240

5

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

SERVICE BULLETIN

In accordance with SRM 51-40-20

1 Remove:

1 Gusset Item (136) Retain

1 Gusset Item (138) Retain

attached with:

4 Screw Item (3) Discard

4 Nut Item (4) Discard

(43) Subtask 536177-831-043-003 - Depending on Inspection results, remove the Frame

Foot from FR45, LH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 45

Manpower Resources

Manhours 16.00

Minimum number of person 2

Subtask elapsed time 8.00

Skills AIRFRAME

References

Structural Repair Manual (SRM) 51-40-20

Fig. A-FJAAC

Replacement of the Frame foot FR45,

LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

(a) Remove the Frame foot from Frame 45, LH side.

Refer to Fig. A-FJAAC

In accordance with SRM 51-40-20

1 Remove:

1 Frame foot Item (108) Discard

2 Stiffener Item (58) Retain

1 Splice Item (72) Retain

4 Rivet Item (19) Discard

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 241

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

SERVICE BULLETIN

29 Screw Item (3) Discard

29 Nut Item (4) Discard

And:

4 Screw Item (55) Retain

4 Nut Item (56) Discard

or

4 Nut Item (76) Discard

And

23 Rivet Item (5) Discard

or

23 Screw Item (93) Discard

23 Nut Item (94) Discard

And if installed, remove:

1 Bracket Item (79) Retain

(44) Subtask 536177-831-044-003 - Depending on Inspection results, install an identical

Frame Foot at FR45, LH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 145

Manpower Resources

Manhours 16.00

Minimum number of person 2

Subtask elapsed time 8.00

Skills AIRFRAME

Material necessary to do the job

Kit 536177A15R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

9 ASNA2529-3 48 NUT

12 ASNA2529-6 2 NUT

16 ASNA2529-5 2 NUT

19 ASNA2050DXJ4020 4 RIVET

23 EN6115V3X5 8 SCREW

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 242

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

SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

24 EN6115V3X7 7 SCREW

25 EN6115V3X6 18 SCREW

26 EN6114V6X14 2 SCREW

28 EN6114V5X8 1 SCREW

39 EN6115V3X9 4 SCREW

40 EN6115V3X8 10 SCREW

41 EN6114V5X10 1 SCREW

46 NAS1726-6E 2 NUT

47 EN6114V3X6 1 SCREW

48 ASNA2001V6-8X 2 SCREW

56 NSA5057-6 4 NUT

76 NSA5057-7 4 NUT

108 A5711113320095 1 FOOT

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant -

General Purpose Brushable

06AAA1 As required

Polysulfide Sealant - Fuel

Tank Brushable

06ABA1 As required

Polysulfide Sealant - Fuel

Tank Fillet

06ABB1 As required

References

Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001

Structural Repair Manual (SRM) 51-40-00

51-40-20

51-40-30

51-40-40

Fig. A-FJAAC

Replacement of the Frame foot FR45,

LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Fig. A-FTAAA

Removal/Installation of the Gussets at

FR45, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

(a) Install and drill all the parts.

Refer to Fig. A-FJAAC

In accordance with SRM 51-40-40

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 243

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

SERVICE BULLETIN

1 Put all the parts in position as shown on Fig. A-FJAAC.

1 Frame foot A5711113320095 Item 108

2 Stiffener Item (58) Retained at

removal

1 Splice Item (72) Retained at

removal

NOTE: If necessary, rework the upper and side surfaces of the Frame

foot with a maximum of 0.5 mm (0.020 in.) as shown on Fig.

A-FJAAC Sheet 03.

NOTE: Between parts apply:

Polysulfide Sealant

- Fuel Tank Fillet

06ABB1 As required

2 Drill the holes of the Frame foot H231 to H254, H257 to H266 and H271 to

H272 to the diameter given on Fig. A-FJAAC Sheet 03 to Fig. A-FJAAC Sheet

05.

3 Drill the holes of the stiffener at STGR 36 H255 and H256 to the diameter

given on Fig. A-FJAAC Sheet 03.

4 Drill the holes of the stiffener at STGR 37 H267 and H268 to the diameter

given on Fig. A-FJAAC Sheet 05.

NOTE: Use the existing holes of the stringers.

5 Drill the holes of the splice H273 to H285 to the diameter given on Fig. AFJAAC Sheet 06.

(b) Install the fasteners.

Fig. A-FJAAC

In accordance with SRM 51-40-00, SRM 51-40-20 and SRM 51-40-30

Refer to AMM 20-21-12, Page Block 001

1 Install the fasteners of the Frame foot H231 to H254, H257 to H266 and H271

to H272:

Refer to Fig. A-FJAAC Sheet 03 to Fig. A-FJAAC Sheet 05

6 Screw EN6115V3X5 Item 23

5 Screw EN6115V3X7 Item 24

16 Screw EN6115V3X6 Item 25

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 244

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@A300-600

SERVICE BULLETIN

3 Screw EN6115V3X9 Item 39

4 Screw EN6115V3X8 Item 40

1 Screw EN6114V3X6 Item 47

2 Screw ASNA2001V6-8X Item 48

35 Nut ASNA2529-3 Item 9

2 Nut NAS1726-6E Item 46

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

2 Install the four upper fasteners of the Frame foot:

Refer to Fig. A-FJAAC Sheet 02

4 Bolt Item (55) Retained at

removal

4 Nut NSA5057-6 Item 56

or

4 Nut NSA5057-7 Item 76

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

3 Install the fasteners of the stiffener at STGR 36 H255 and H256:

Refer to Fig. A-FJAAC Sheet 03

2 Rivet ASNA2050DXJ4020 Item 19

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 245

5

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

SERVICE BULLETIN

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

4 Install the fasteners of the stiffener at STGR 37 H267 and H268:

Refer to Fig. A-FJAAC Sheet 05

2 Rivet ASNA2050DXJ4020 Item 19

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

5 Install the fasteners of the splice H273 to H285:

Refer to Fig. A-FJAAC Sheet 06

2 Screw EN6115V3X7 Item 24

2 Screw EN6115V3X5 Item 23

1 Screw EN6115V3X9 Item 39

6 Screw EN6115V3X8 Item 40

13 Nut ASNA2529-3 Item 9

2 Screw EN6115V3X6 Item 25

And if removed, install:

1 Bracket Item (79) Retained at

removal

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 246

5

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

SERVICE BULLETIN

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

6 Do a sealant bead around the parts with:

Polysulfide Sealant

- Fuel Tank Fillet

06ABB1 As required

(c) Install the Gussets at Frame 45, LH side.

Refer to Fig. A-FTAAA

In accordance with SRM 51-40-20, SRM 51-40-00, SRM 51-40-30 and SRM

51-40-40

Refer to AMM 20-21-12, Page Block 001

1 Put the gussets in position as shown on Fig. A-FTAAA.

1 Gusset Item (136) Retained at

removal

1 Gusset Item (138) Retained at

removal

NOTE: Between the Frame foot and the aft gusset, the distance must

be 2 times the thickness of the gusset.

NOTE: Between the Frame foot and the FWD gusset, the distance

must be 1.3 times the thickness of the gusset.

2 Drill holes H269 and H270 to the diameter given on Fig. A-FTAAA Sheet 03.

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

4 Install:

1 Gusset Item (136) Retained at

removal

1 Gusset Item (138) Retained at

removal

2 Screw EN6114V6X14 Item 26

1 Screw EN6114V5X8 Item 28

1 Screw EN6114V5X10 Item 41

2 Nut ASNA2529-6 Item 12

2 Nut ASNA2529-5 Item 16

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 247

5

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

SERVICE BULLETIN

(45) Subtask 536177-831-045-001 - Depending on Inspection results, if removed, install

the Fasteners at FR45, LH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 45

Manpower Resources

Manhours 6.00

Minimum number of person 2

Subtask elapsed time 3.00

Skills AIRFRAME

Material necessary to do the job

Component COMPA04

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

9 ASNA2529-3 32 NUT

47 EN6114V3X6 32 SCREW

90 ASNA2019-56-25 32 RIVET

92 EN6080D6X-32 20 RIVET

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

NOTE: The components listed above are only necessary if crack is found on a

Frame foot. The quantity of these items are to be ordered as required.

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant - Fuel

Tank Brushable

06ABA1 As required

References

Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001

Structural Repair Manual (SRM) 51-24-00

51-40-00

51-40-20

51-40-30

Fig. A-FVAAA

Removal/Installation of the Fasteners

from FR41 to FR46, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 248

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@A300-600

SERVICE BULLETIN

(a) If removed, install the fasteners at Frame 45, LH side.

Refer to Fig. A-FVAAA

In accordance with SRM 51-40-20, SRM 51-24-00, SRM 51-40-00 and SRM

51-40-30

Refer to AMM 20-21-12, Page Block 001

1 Install:

20 Rivet EN6080D6X-32 Item 92

And:

32 Rivet ASNA2019-56-25 Item 90

or

32 Screw EN6114V3X6 Item 47

32 Nut ASNA2529-3 Item 9

NOTE: Protect the fasteners with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

(46) Subtask 536177-831-046-001 - Depending on Inspection results, if necessary,

remove the Fasteners from FR45, RH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 45

Manpower Resources

Manhours 4.00

Minimum number of person 2

Subtask elapsed time 2.00

Skills AIRFRAME

References

Structural Repair Manual (SRM) 51-40-20

Fig. A-FVAAA

Removal/Installation of the Fasteners

from FR41 to FR46, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 249

5

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

SERVICE BULLETIN

(a) If necessary, to ease the replacement of the Frame foot, remove fasteners from

Frame 45, RH side.

Refer to Fig. A-FVAAA

In accordance with SRM 51-40-20

1 Remove:

20 Rivet Item (19) Discard

And:

32 Rivet Item (5) Discard

or

32 Bolt Item (3) Discard

32 Nut Item (4) Discard

(47) Subtask 536177-831-047-001 - Depending on Inspection results, remove the

Gussets from FR45, RH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 45

Manpower Resources

Manhours 1.00

Minimum number of person 2

Subtask elapsed time 1.00

Skills AIRFRAME

References

Structural Repair Manual (SRM) 51-40-20

Fig. A-FTAAA

Removal/Installation of the Gussets at

FR45, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

(a) Remove the Gussets from Frame 45, RH side.

Refer to Fig. A-FTAAA

In accordance with SRM 51-40-20

1 Remove:

1 Gusset Item (137) Retain

1 Gusset Item (139) Retain

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 250

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@A300-600

SERVICE BULLETIN

attached with:

4 Screw Item (3) Discard

4 Nut Item (4) Discard

(48) Subtask 536177-831-048-003 - Depending on Inspection results, remove the Frame

Foot from FR45, RH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 45

Manpower Resources

Manhours 16.00

Minimum number of person 2

Subtask elapsed time 8.00

Skills AIRFRAME

References

Structural Repair Manual (SRM) 51-40-20

Fig. A-FJAAC

Replacement of the Frame foot FR45,

LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

(a) Remove the Frame foot from Frame 45, RH side.

Refer to Fig. A-FJAAC

In accordance with SRM 51-40-20

1 Remove:

1 Frame foot Item (109) Discard

2 Stiffener Item (57) Retain

1 Splice Item (71) Retain

4 Rivet Item (19) Discard

29 Screw Item (3) Discard

29 Nut Item (4) Discard

And:

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 251

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@A300-600

SERVICE BULLETIN

4 Screw Item (55) Retain

4 Nut Item (56) Discard

or

4 Nut Item (76) Discard

And:

23 Rivet Item (5) Discard

or

23 Screw Item (93) Discard

23 Nut Item (94) Discard

(49) Subtask 536177-831-049-003 - Depending on Inspection results, install an identical

Frame Foot at FR45, RH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 45

Manpower Resources

Manhours 16.00

Minimum number of person 2

Subtask elapsed time 8.00

Skills AIRFRAME

Material necessary to do the job

Kit 536177A33R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

9 ASNA2529-3 48 NUT

12 ASNA2529-6 2 NUT

16 ASNA2529-5 2 NUT

19 ASNA2050DXJ4020 4 RIVET

23 EN6115V3X5 10 SCREW

24 EN6115V3X7 7 SCREW

25 EN6115V3X6 16 SCREW

26 EN6114V6X14 2 SCREW

28 EN6114V5X8 1 SCREW

39 EN6115V3X9 4 SCREW

40 EN6115V3X8 10 SCREW

41 EN6114V5X10 1 SCREW

46 NAS1726-6E 2 NUT

47 EN6114V3X6 1 SCREW

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 252

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@A300-600

SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

48 ASNA2001V6-8X 2 SCREW

56 NSA5057-6 4 NUT

76 NSA5057-7 4 NUT

109 A5711113320195 1 FOOT

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant -

General Purpose Brushable

06AAA1 As required

Polysulfide Sealant - Fuel

Tank Brushable

06ABA1 As required

Polysulfide Sealant - Fuel

Tank Fillet

06ABB1 As required

References

Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001

Structural Repair Manual (SRM) 51-40-00

51-40-20

51-40-30

51-40-40

Fig. A-FJAAC

Replacement of the Frame foot FR45,

LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Fig. A-FTAAA

Removal/Installation of the Gussets at

FR45, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

(a) Install and drill all the parts.

Refer to Fig. A-FJAAC

In accordance with SRM 51-40-40

1 Put all the parts in position as shown on Fig. A-FJAAC.

1 Frame foot A5711113320195 Item 109

2 Stiffener Item (57) Retained at

removal

1 Splice Item (71) Retained at

removal

NOTE: If necessary, rework the upper and side surfaces of the Frame

foot with a maximum of 0.5 mm (0.020 in.) as shown on Fig.

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 253

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@A300-600

SERVICE BULLETIN

A-FJAAC Sheet 03.

NOTE: Between parts apply:

Polysulfide Sealant

- Fuel Tank Fillet

06ABB1 As required

2 Drill the holes of the Frame foot H231 to H254, H257 to H266 and H271 to

H272 to the diameter given on Fig. A-FJAAC Sheet 03 to Fig. A-FJAAC Sheet

05.

3 Drill the holes of the stiffener at STGR 36 H255 and H256 to the diameter

given on Fig. A-FJAAC Sheet 03.

4 Drill the holes of the stiffener at STGR 37 H267 and H268 to the diameter

given on Fig. A-FJAAC Sheet 05.

NOTE: Use the existing holes of the stringers.

5 Drill the holes of the splice H273 to H285 to the diameter given on Fig. AFJAAC Sheet 06.

(b) Install the fasteners.

Fig. A-FJAAC

In accordance with SRM 51-40-00, SRM 51-40-20 and SRM 51-40-30

Refer to AMM 20-21-12, Page Block 001

1 Install the fasteners of the Frame foot H231 to H254, H257 to H266 and H271

to H272:

Refer to Fig. A-FJAAC Sheet 03 to Fig. A-FJAAC Sheet 05

6 Screw EN6115V3X5 Item 23

5 Screw EN6115V3X7 Item 24

16 Screw EN6115V3X6 Item 25

3 Screw EN6115V3X9 Item 39

4 Screw EN6115V3X8 Item 40

1 Screw EN6114V3X6 Item 47

2 Screw ASNA2001V6-8X Item 48

35 Nut ASNA2529-3 Item 9

2 Nut NAS1726-6E Item 46

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 254

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@A300-600

SERVICE BULLETIN

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

2 Install the four upper fasteners of the Frame foot:

Refer to Fig. A-FJAAC Sheet 02

4 Bolt Item (55) Retained at

removal

4 Nut NSA5057-6 Item 56

or

4 Nut NSA5057-7 Item 76

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

3 Install the fasteners of the stiffener at STGR 36 H255 and H256:

Refer to Fig. A-FJAAC Sheet 03

2 Rivet ASNA2050DXJ4020 Item 19

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

4 Install the fasteners of the stiffener at STGR 37 H267 and H268:

Refer to Fig. A-FJAAC Sheet 05

2 Rivet ASNA2050DXJ4020 Item 19

NOTE: Wet install the fasteners with:

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 255

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@A300-600

SERVICE BULLETIN

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

5 Install the fasteners of the splice H273 to H285:

Refer to Fig. A-FJAAC Sheet 06

2 Screw EN6115V3X7 Item 24

4 Screw EN6115V3X5 Item 23

1 Screw EN6115V3X9 Item 39

6 Screw EN6115V3X8 Item 40

13 Nut ASNA2529-3 Item 9

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

6 Do a sealant bead around the parts with:

Polysulfide Sealant

- Fuel Tank Fillet

06ABB1 As required

(c) Install the Gussets at Frame 45, LH side.

Refer to Fig. A-FTAAA

In accordance with SRM 51-40-20, SRM 51-40-00, SRM 51-40-30 and SRM

51-40-40

Refer to AMM 20-21-12, Page Block 001

1 Put the gussets in position as shown on Fig. A-FTAAA.

1 Gusset Item (137) Retained at

removal

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 256

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@A300-600

SERVICE BULLETIN

1 Gusset Item (139) Retained at

removal

NOTE: Between the Frame foot and the aft gusset, the distance must

be 2 times the thickness of the gusset.

NOTE: Between the Frame foot and the FWD gusset, the distance

must be 1.3 times the thickness of the gusset.

2 Drill holes H269 and H270 to the diameter given on Fig. A-FTAAA Sheet 03.

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

4 Install:

1 Gusset Item (137) Retained at

removal

1 Gusset Item (139) Retained at

removal

2 Screw EN6114V6X14 Item 26

1 Screw EN6114V5X8 Item 28

1 Screw EN6114V5X10 Item 41

2 Nut ASNA2529-6 Item 12

2 Nut ASNA2529-5 Item 16

(50) Subtask 536177-831-050-001 - Depending on Inspection results, install the

Fasteners at FR45, RH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 45

Manpower Resources

Manhours 6.00

Minimum number of person 2

Subtask elapsed time 3.00

Skills AIRFRAME

Material necessary to do the job

Component COMPA04

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

9 ASNA2529-3 32 NUT

47 EN6114V3X6 32 SCREW

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 257

5

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

SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

90 ASNA2019-56-25 32 RIVET

92 EN6080D6X-32 20 RIVET

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

NOTE: The components listed above are only necessary if crack is found on a

Frame foot. The quantity of these items are to be ordered as required.

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant - Fuel

Tank Brushable

06ABA1 As required

References

Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001

Structural Repair Manual (SRM) 51-24-00

51-40-00

51-40-20

51-40-30

Fig. A-FVAAA

Removal/Installation of the Fasteners

from FR41 to FR46, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

(a) If removed, install the fasteners at Frame 45, RH side.

Refer to Fig. A-FVAAA

In accordance with SRM 51-40-20, SRM 51-24-00, SRM 51-40-00 and SRM

51-40-30

Refer to AMM 20-21-12, Page Block 001

1 Install:

20 Rivet EN6080D6X-32 Item 92

And:

32 Rivet ASNA2019-56-25 Item 90

or

32 Screw EN6114V3X6 Item 47

32 Nut ASNA2529-3 Item 9

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 258

5

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@A300-600

SERVICE BULLETIN

NOTE: Protect the fasteners with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

(51) Subtask 536177-831-051-001 - Depending on Inspection results, if necessary,

remove the Fasteners from FR46, LH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 46

Manpower Resources

Manhours 4.00

Minimum number of person 2

Subtask elapsed time 2.00

Skills AIRFRAME

References

Structural Repair Manual (SRM) 51-40-20

Fig. A-FVAAA

Removal/Installation of the Fasteners

from FR41 to FR46, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

(a) If necessary, to ease the replacement of the Frame foot, remove fasteners from

Frame 46, LH side.

Refer to Fig. A-FVAAA

In accordance with SRM 51-40-20

1 Remove:

16 Rivet Item (19) Discard

And:

24 Rivet Item (5) Discard

or

24 Bolt Item (3) Discard

24 Nut Item (4) Discard

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 259

5

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@A300-600

SERVICE BULLETIN

(52) Subtask 536177-831-052-001 - Depending on Inspection results, remove the

Gussets from FR46, LH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 46

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills AIRFRAME

References

Structural Repair Manual (SRM) 51-40-20

Fig. A-FUAAA

Removal/Installation of the Gussets at

FR46, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

(a) Remove the Gussets from Frame 46, LH side.

Refer to Fig. A-FUAAA

In accordance with SRM 51-40-20

1 Remove:

1 Gusset Item (140) Retain

1 Gusset Item (142) Retain

attached with:

4 Screw Item (3) Discard

4 Nut Item (4) Discard

(53) Subtask 536177-831-053-003 - Depending on Inspection results, remove the Frame

Foot from FR46, LH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 46

Manpower Resources

Manhours 16.00

Minimum number of person 2

Subtask elapsed time 8.00

Skills AIRFRAME

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 260

5

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@A300-600

SERVICE BULLETIN

References

Structural Repair Manual (SRM) 51-40-20

Fig. A-FKAAC

Replacement of the Frame foot FR46,

LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

(a) Remove the Frame foot from Frame 46, LH side.

Refer to Fig. A-FKAAC

In accordance with SRM 51-40-20

1 Remove:

1 Frame foot Item (110) Discard

1 Stiffener Item (58) Retain

1 Splice Item (82) Retain

2 Rivet Item (19) Discard

37 Screw Item (3) Discard

37 Nut Item (4) Discard

And:

4 Screw Item (55) Retain

4 Nut Item (56) Discard

or

4 Nut Item (76) Discard

And:

16 Rivet Item (5) Discard

or

16 Screw Item (93) Discard

16 Nut Item (94) Discard

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 261

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@A300-600

SERVICE BULLETIN

(54) Subtask 536177-831-054-003 - Depending on Inspection results, install an identical

Frame Foot at FR46, LH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 46

Manpower Resources

Manhours 16.00

Minimum number of person 1

Subtask elapsed time 8.00

Skills AIRFRAME

Material necessary to do the job

Kit 536177A18R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

9 ASNA2529-3 43 NUT

12 ASNA2529-6 3 NUT

14 NAS1726-5E 2 NUT

16 ASNA2529-5 7 NUT

19 ASNA2050DXJ4020 2 RIVET

23 EN6115V3X5 12 SCREW

24 EN6115V3X7 10 SCREW

25 EN6115V3X6 19 SCREW

26 EN6114V6X14 1 SCREW

28 EN6114V5X8 6 SCREW

29 EN6115V3X4 2 SCREW

52 EN6114V6X17 2 SCREW

53 ASNA2001V5-12X 2 SCREW

54 EN6114V5X12 1 SCREW

56 NSA5057-6 4 NUT

76 NSA5057-7 4 NUT

110 A5711113420095 1 FOOT

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant -

General Purpose Brushable

06AAA1 As required

Polysulfide Sealant - Fuel

Tank Brushable

06ABA1 As required

Polysulfide Sealant - Fuel

Tank Fillet

06ABB1 As required

References

Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 262

5

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@A300-600

SERVICE BULLETIN

References

Structural Repair Manual (SRM) 51-40-00

51-40-20

51-40-30

51-40-40

Fig. A-FKAAC

Replacement of the Frame foot FR46,

LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Fig. A-FUAAA

Removal/Installation of the Gussets at

FR46, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

(a) Install and drill all the parts.

Refer to Fig. A-FKAAC

In accordance with SRM 51-40-40

1 Put all the parts in position as shown on Fig. A-FKAAC.

1 Frame foot A5711113420095 Item 110

1 Stiffener Item (58) Retained at

removal

1 Splice Item (82) Retained at

removal

NOTE: If necessary, rework the upper and side surfaces of the Frame

foot with a maximum of 0.5 mm (0.020 in.) as shown on Fig.

A-FKAAC Sheet 03.

NOTE: Between parts apply:

Polysulfide Sealant

- Fuel Tank Fillet

06ABB1 As required

2 Drill the holes of the Frame foot H300 to H313, H316 to H331 and H334 to

H341 to H313 and H316 to H341 to the diameter given on Fig. A-FKAAC

Sheet 03 to Fig. A-FKAAC Sheet 05.

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

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

(b) Install the fasteners.

Fig. A-FKAAC

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 263

5

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@A300-600

SERVICE BULLETIN

In accordance with SRM 51-40-00, SRM 51-40-20 and SRM 51-40-30

Refer to AMM 20-21-12, Page Block 001

1 Install the fasteners of the Frame foot H300 to H313, H316 to H331 and H334

to H341 to H313 and H316 to H341:

Refer to Fig. A-FKAAC Sheet 03 to Fig. A-FKAAC Sheet 05

5 Screw EN6115V3X5 Item 23

9 Screw EN6115V3X7 Item 24

16 Screw EN6115V3X6 Item 25

6 Screw EN6114V5X8 Item 28

2 Screw ASNA2001V5-12X Item 53

30 Nut ASNA2529-3 Item 9

2 Nut NAS1726-5E Item 14

6 Nut ASNA2529-5 Item 16

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

2 Install the four upper fasteners of the Frame foot:

Refer to Fig. A-FKAAC Sheet 02

4 Bolt Item (55) Retained at

removal

4 Nut NSA5057-6 Item 56

or

4 Nut NSA5057-7 Item 76

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 264

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@A300-600

SERVICE BULLETIN

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

3 Install the fasteners of the stiffener at STGR 37 H314 and H315:

Refer to Fig. A-FKAAC Sheet 05

2 Rivet ASNA2050DXJ4020 Item 19

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

4 Install the fasteners of the splice H342 to H354:

Refer to Fig. A-FKAAC Sheet 06

7 Screw EN6115V3X5 Item 23

1 Screw EN6115V3X7 Item 24

3 Screw EN6115V3X6 Item 25

2 Screw EN6115V3X4 Item 29

13 Nut ASNA2529-3 Item 9

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

5 Do a sealant bead around the parts with:

Polysulfide Sealant

- Fuel Tank Fillet

06ABB1 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 265

5

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@A300-600

SERVICE BULLETIN

(c) Install the Gussets at Frame 46, LH side.

Refer to Fig. A-FUAAA

In accordance with SRM 51-40-20, SRM 51-40-00, SRM 51-40-30 and SRM

51-40-40

Refer to AMM 20-21-12, Page Block 001

1 Put the gussets in position as shown on Fig. A-FUAAA.

1 Gusset Item (140) Retained at

removal

1 Gusset Item (142) Retained at

removal

NOTE: Between the Frame foot and the aft gusset, the distance must

be 2 times the thickness of the gusset.

NOTE: Between the Frame foot and the FWD gusset, the distance

must be 1.3 times the thickness of the gusset.

2 Drill holes H332 and H333 to the diameter given on Fig. A-FUAAA Sheet 03.

3 Drill holes H355 and H356 to the diameter given on Fig. A-FUAAA Sheet 03.

4 Install:

1 Gusset Item (140) Retained at

removal

1 Gusset Item (142) Retained at

removal

1 Screw EN6114V6X14 Item 26

2 Screw EN6114V6X17 Item 52

1 Screw EN6114V5X12 Item 54

3 Nut ASNA2529-6 Item 12

1 Nut ASNA2529-5 Item 16

(55) Subtask 536177-831-055-001 - Depending on Inspection results, if removed, install

the Fasteners at FR46, LH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 46

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 266

5

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

SERVICE BULLETIN

Manpower Resources

Manhours 6.00

Minimum number of person 2

Subtask elapsed time 3.00

Skills AIRFRAME

Material necessary to do the job

Component COMPA05

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

9 ASNA2529-3 24 NUT

47 EN6114V3X6 16 SCREW

90 ASNA2019-56-25 24 RIVET

91 EN6114V3X5 8 SCREW

92 EN6080D6X-32 16 RIVET

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

NOTE: The components listed above are only necessary if crack is found on a

Frame foot. The quantity of these items are to be ordered as required.

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant - Fuel

Tank Brushable

06ABA1 As required

References

Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001

Structural Repair Manual (SRM) 51-24-00

51-40-00

51-40-20

51-40-30

Fig. A-FVAAA

Removal/Installation of the Fasteners

from FR41 to FR46, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

(a) If removed, install the fasteners at Frame 46, LH side.

Refer to Fig. A-FVAAA

In accordance with SRM 51-40-20, SRM 51-24-00, SRM 51-40-00 and SRM

51-40-30

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 267

5

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

SERVICE BULLETIN

Refer to AMM 20-21-12, Page Block 001

1 Install:

16 Rivet EN6080D6X-32 Item 92

And:

16 Rivet ASNA2019-56-25 Item 90

or

16 Screw EN6114V3X6 Item 47

16 Nut ASNA2529-3 Item 9

And:

8 Rivet ASNA2019-56-25 Item 90

or

8 Screw EN6114V3X5 Item 91

8 Nut ASNA2529-3 Item 9

NOTE: Protect the fasteners with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

(56) Subtask 536177-831-056-001 - Depending on Inspection results, if necessary,

remove the Fasteners from FR46, RH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 46

Manpower Resources

Manhours 4.00

Minimum number of person 2

Subtask elapsed time 2.00

Skills AIRFRAME

References

Structural Repair Manual (SRM) 51-40-20

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 268

5

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

SERVICE BULLETIN

References

Fig. A-FVAAA

Removal/Installation of the Fasteners

from FR41 to FR46, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

(a) If necessary, to ease the replacement of the Frame foot, remove fasteners from

Frame 46, RH side.

Refer to Fig. A-FVAAA

In accordance with SRM 51-40-20

1 Remove:

16 Rivet Item (19) Discard

And:

24 Rivet Item (5) Discard

or

24 Bolt Item (3) Discard

24 Nut Item (4) Discard

(57) Subtask 536177-831-057-001 - Depending on Inspection results, remove the

Gussets from FR46, RH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 46

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills AIRFRAME

References

Structural Repair Manual (SRM) 51-40-20

Fig. A-FUAAA

Removal/Installation of the Gussets at

FR46, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

(a) Remove the Gussets from Frame 46, RH side.

Refer to Fig. A-FUAAA

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 269

5

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

SERVICE BULLETIN

In accordance with SRM 51-40-20

1 Remove:

1 Gusset Item (141) Retain

1 Gusset Item (143) Retain

attached with:

4 Screw Item (3) Discard

4 Nut Item (4) Discard

(58) Subtask 536177-831-058-003 - Depending on Inspection results, remove the Frame

Foot from FR46, RH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 46

Manpower Resources

Manhours 16.00

Minimum number of person 2

Subtask elapsed time 8.00

Skills AIRFRAME

References

Structural Repair Manual (SRM) 51-40-20

Fig. A-FKAAC

Replacement of the Frame foot FR46,

LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

(a) Remove the Frame foot from Frame 46, RH side.

Refer to Fig. A-FKAAC

In accordance with SRM 51-40-20

1 Remove:

1 Frame foot Item (111) Discard

1 Stiffener Item (57) Retain

1 Splice Item (83) Retain

2 Rivet Item (19) Discard

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 270

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@A300-600

SERVICE BULLETIN

37 Screw Item (3) Discard

37 Nut Item (4) Discard

And:

4 Screw Item (55) Retain

4 Nut Item (56) Discard

or

4 Nut Item (76) Discard

And:

16 Rivet Item (5) Discard

or

16 Screw Item (93) Discard

16 Nut Item (94) Discard

(59) Subtask 536177-831-059-003 - Depending on Inspection results, install an identical

Frame Foot at FR46, RH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 46

Manpower Resources

Manhours 16.00

Minimum number of person 2

Subtask elapsed time 8.00

Skills AIRFRAME

Material necessary to do the job

Kit 536177A36R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

9 ASNA2529-3 43 NUT

12 ASNA2529-6 3 NUT

14 NAS1726-5E 2 NUT

16 ASNA2529-5 7 NUT

19 ASNA2050DXJ4020 2 RIVET

23 EN6115V3X5 12 SCREW

24 EN6115V3X7 10 SCREW

25 EN6115V3X6 19 SCREW

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 271

5

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

SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

26 EN6114V6X14 1 SCREW

28 EN6114V5X8 6 SCREW

29 EN6115V3X4 2 SCREW

52 EN6114V6X17 2 SCREW

53 ASNA2001V5-12X 2 SCREW

54 EN6114V5X12 1 SCREW

56 NSA5057-6 4 NUT

76 NSA5057-7 4 NUT

111 A5711113420195 1 FOOT

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant -

General Purpose Brushable

06AAA1 As required

Polysulfide Sealant - Fuel

Tank Brushable

06ABA1 As required

Polysulfide Sealant - Fuel

Tank Fillet

06ABB1 As required

References

Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001

Structural Repair Manual (SRM) 51-40-00

51-40-20

51-40-30

51-40-40

Fig. A-FKAAC

Replacement of the Frame foot FR46,

LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Fig. A-FUAAA

Removal/Installation of the Gussets at

FR46, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

(a) Install and drill all the parts.

Refer to Fig. A-FKAAC

In accordance with SRM 51-40-40

1 Put all the parts in position as shown on Fig. A-FKAAC.

1 Frame foot A5711113420195 Item 111

1 Stiffener Item (57) Retained at

removal

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 272

5

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@A300-600

SERVICE BULLETIN

1 Splice Item (83) Retained at

removal

NOTE: If necessary, rework the upper and side surfaces of the Frame

foot with a maximum of 0.5 mm (0.020 in.) as shown on Fig.

A-FKAAC Sheet 03.

NOTE: Between parts apply:

Polysulfide Sealant

- Fuel Tank Fillet

06ABB1 As required

2 Drill the holes of the Frame foot H300 to H313, H316 to H331 and H334 to

H341 to H313 and H316 to H341 to the diameter given on Fig. A-FKAAC

Sheet 03 to Fig. A-FKAAC Sheet 05.

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

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

(b) Install the fasteners.

Fig. A-FKAAC

In accordance with SRM 51-40-00, SRM 51-40-20 and SRM 51-40-30

Refer to AMM 20-21-12, Page Block 001

1 Install the fasteners of the Frame foot H300 to H313, H316 to H331 and H334

to H341 to H313 and H316 to H341:

Refer to Fig. A-FKAAC Sheet 03 to Fig. A-FKAAC Sheet 05

5 Screw EN6115V3X5 Item 23

9 Screw EN6115V3X7 Item 24

16 Screw EN6115V3X6 Item 25

6 Screw EN6114V5X8 Item 28

2 Screw ASNA2001V5-12X Item 53

30 Nut ASNA2529-3 Item 9

2 Nut NAS1726-5E Item 14

6 Nut ASNA2529-5 Item 16

NOTE: Protect the fasteners head and nuts with:

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 273

5

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@A300-600

SERVICE BULLETIN

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

2 Install the four upper fasteners of the Frame foot:

Refer to Fig. A-FKAAC Sheet 02

4 Bolt Item (55) Retained at

removal

4 Nut NSA5057-6 Item 56

or

4 Nut NSA5057-7 Item 76

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

3 Install the fasteners of the stiffener at STGR 37 H314 and H315:

Refer to Fig. A-FKAAC Sheet 05

2 Rivet ASNA2050DXJ4020 Item 19

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

4 Install the fasteners of the splice H342 to H354:

Refer to Fig. A-FKAAC Sheet 06

7 Screw EN6115V3X5 Item 23

1 Screw EN6115V3X7 Item 24

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 274

5

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

SERVICE BULLETIN

3 Screw EN6115V3X6 Item 25

2 Screw EN6115V3X4 Item 29

13 Nut ASNA2529-3 Item 9

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

5 Do a sealant bead around the parts with:

Polysulfide Sealant

- Fuel Tank Fillet

06ABB1 As required

(c) Install the Gussets at Frame 46, LH side.

Refer to Fig. A-FUAAA

In accordance with SRM 51-40-20, SRM 51-40-00, SRM 51-40-30 and SRM

51-40-40

Refer to AMM 20-21-12, Page Block 001

1 Put the gussets in position as shown on Fig. A-FUAAA.

1 Gusset Item (141) Retained at

removal

1 Gusset Item (143) Retained at

removal

NOTE: Between the Frame foot and the aft gusset, the distance must

be 2 times the thickness of the gusset.

NOTE: Between the Frame foot and the FWD gusset, the distance

must be 1.3 times the thickness of the gusset.

2 Drill holes H332 and H333 to the diameter given on Fig. A-FUAAA Sheet 03.

3 Drill holes H355 and H356 to the diameter given on Fig. A-FUAAA Sheet 03.

4 Install:

1 Gusset Item (141) Retained at

removal

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 275

5

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

SERVICE BULLETIN

1 Gusset Item (143) Retained at

removal

1 Screw EN6114V6X14 Item 26

2 Screw EN6114V6X17 Item 52

1 Screw EN6114V5X12 Item 54

3 Nut ASNA2529-6 Item 12

1 Nut ASNA2529-5 Item 16

(60) Subtask 536177-831-060-001 - Depending on Inspection results, install the

Fasteners at FR46, RH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 46

Manpower Resources

Manhours 6.00

Minimum number of person 2

Subtask elapsed time 3.00

Skills AIRFRAME

Material necessary to do the job

Component COMPA05

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

9 ASNA2529-3 24 NUT

47 EN6114V3X6 16 SCREW

90 ASNA2019-56-25 24 RIVET

91 EN6114V3X5 8 SCREW

92 EN6080D6X-32 16 RIVET

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

NOTE: The components listed above are only necessary if crack is found on a

Frame foot. The quantity of these items are to be ordered as required.

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant - Fuel

Tank Brushable

06ABA1 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 276

5

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

SERVICE BULLETIN

References

Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001

Structural Repair Manual (SRM) 51-24-00

51-40-00

51-40-20

51-40-30

Fig. A-FVAAA

Removal/Installation of the Fasteners

from FR41 to FR46, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

(a) If removed, install the fasteners at Frame 46, RH side.

Refer to Fig. A-FVAAA

In accordance with SRM 51-40-20, SRM 51-24-00, SRM 51-40-00 and SRM

51-40-30

Refer to AMM 20-21-12, Page Block 001

1 Install:

16 Rivet EN6080D6X-32 Item 92

And:

16 Rivet ASNA2019-56-25 Item 90

or

16 Screw EN6114V3X6 Item 47

16 Nut ASNA2529-3 Item 9

And:

8 Rivet ASNA2019-56-25 Item 90

or

8 Screw EN6114V3X5 Item 91

8 Nut ASNA2529-3 Item 9

NOTE: Protect the fasteners with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 277

5

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

SERVICE BULLETIN

**CONF 002

(1) Subtask 536177-831-001-001 - Depending on Inspection results, if necessary,

remove the Fasteners from FR41, LH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 41

Manpower Resources

Manhours 4.00

Minimum number of person 2

Subtask elapsed time 2.00

Skills AIRFRAME

References

Structural Repair Manual (SRM) 51-40-20

Fig. A-FVAAA

Removal/Installation of the Fasteners

from FR41 to FR46, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

(a) If necessary, to ease the replacement of the Frame foot, remove fasteners from

Frame 41, LH side.

Refer to Fig. A-FVAAA

In accordance with SRM 51-40-20

1 Remove:

20 Rivet Item (19) Discard

And:

32 Rivet Item (5) Discard

or

32 Bolt Item (3) Discard

32 Nut Item (4) Discard

(2) Subtask 536177-831-002-002 - Depending on Inspection results, remove the

Gussets from FR41, LH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 41

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 278

5

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

SERVICE BULLETIN

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills AIRFRAME

References

Structural Repair Manual (SRM) 51-40-20

Fig. A-FLAAB

Removal/Installation of the Gussets at

FR41, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

(a) Remove the Gussets from Frame 41, LH side.

Refer to Fig. A-FLAAB

In accordance with SRM 51-40-20

1 Remove:

1 Gusset Item (120) Retain

1 Gusset Item (122) Retain

attached with:

2 Pin Item (1) Discard

2 Collar Item (2) Discard

2 Screw Item (3) Discard

2 Nut Item (4) Discard

(3) Subtask 536177-831-003-002 - Depending on Inspection results, remove the Frame

Foot from FR41, LH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 41

Manpower Resources

Manhours 16.00

Minimum number of person 2

Subtask elapsed time 8.00

Skills AIRFRAME

References

Structural Repair Manual (SRM) 51-40-20

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 279

5

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@A300-600

SERVICE BULLETIN

References

Fig. A-FCAAB

Replacement of the Frame foot FR41,

LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

(a) Remove the Frame foot from Frame 41, LH side.

Refer to Fig. A-FCAAB

In accordance with SRM 51-40-20

1 Remove:

1 Frame foot Item (100) Discard

1 Stiffener Item (58) Retain

1 Splice Item (60) Retain

1 Shim Item (61) Retain

4 Screw Item (55) Retain

4 Nut Item (56) Discard

42 Pin Item (1) Discard

42 Collar Item (2) Discard

2 Screw Item (3) Discard

2 Nut Item (4) Discard

2 Rivet Item (5) Discard

(4) Subtask 536177-831-004-002 - Depending on Inspection results, install an identical

Frame Foot at FR41, LH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 41

Manpower Resources

Manhours 16.00

Minimum number of person 2

Subtask elapsed time 8.00

Skills AIRFRAME

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 280

5

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

SERVICE BULLETIN

Material necessary to do the job

Kit 536177A02R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

8 EN6115V3A7 15 SCREW

9 ASNA2529-3 36 NUT

10 EN6115V3A6 9 SCREW

11 EN6114V6Y14 4 SCREW

12 ASNA2529-6 4 NUT

13 ASNA2001V5-8Y 2 SCREW

14 NAS1726-5E 2 NUT

15 EN6114V5Y8 4 SCREW

16 ASNA2529-5 4 NUT

17 EN6115V3A5 10 SCREW

18 EN6115V3A4 2 SCREW

19 ASNA2050DXJ4020 2 RIVET

20 EN6114V4Y9 1 SCREW

21 ASNA2529-4 2 NUT

22 EN6114V4Y10 1 SCREW

56 NSA5057-6 4 NUT

100 A5711112920095 1 FOOT

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Wash Primer - Structure 04CMA2 As required

Primer Polyurethane Paint -

Corrosion Inhibiting

04EAC2 As required

Polysulfide Sealant -

General Purpose Brushable

06AAA1 As required

Polysulfide Sealant - Fuel

Tank Brushable

06ABA1 As required

Polysulfide Sealant - Fuel

Tank Fillet

06ABB1 As required

References

Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001

Structural Repair Manual (SRM) 51-40-00

51-40-20

51-40-30

51-40-40

Fig. A-FCAAB

Replacement of the Frame foot FR41,

LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 281

5

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

SERVICE BULLETIN

References

Fig. A-FLAAB

Removal/Installation of the Gussets at

FR41, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

(a) Install and drill all the parts.

Refer to Fig. A-FCAAB

In accordance with SRM 51-40-40

1 Put all the parts in position as shown on Fig. A-FCAAB.

1 Frame foot A5711112920095 Item 100

1 Stiffener Item (58) Retained at

removal

1 Splice Item (60) Retained at

removal

1 Shim Item (61) Retained at

removal

NOTE: If necessary, rework the upper and side surfaces of the Frame

foot with a maximum of 0.5 mm (0.020 in.) as shown on Fig.

A-FCAAB Sheet 03.

NOTE: Between parts apply:

Polysulfide Sealant

- Fuel Tank Fillet

06ABB1 As required

2 Drill the holes of the Frame foot H1 to H23 and H26 to H31 to the diameter

given on Fig. A-FCAAB Sheet 03 and Fig. A-FCAAB Sheet 04.

3 Drill the holes of the stiffener H45 and H46 to the diameter given on Fig. AFCAAB Sheet 04.

4 Drill the holes of the splice H32 to H44 to the diameter given on Fig. A-FCAAB

Sheet 05.

(b) Cut-out the Frame foot Item 100 as shown on Fig. A-FCAAB Sheet 03.

Protect the cut-out with:

Wash Primer -

Structure

04CMA2 As required

Primer

Polyurethane Paint

- Corrosion

Inhibiting

04EAC2 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 282

5

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@A300-600

SERVICE BULLETIN

(c) Install the fasteners.

Refer to Fig. A-FCAAB

In accordance with SRM 51-40-00, SRM 51-40-20 and SRM 51-40-30

Refer to AMM 20-21-12, Page Block 001

1 Install the fasteners of the Frame foot H1 to H31:

Refer to Fig. A-FCAAB Sheet 03 and Fig. A-FCAAB Sheet 04

14 Screw EN6115V3A7 Item 8

9 Screw EN6115V3A6 Item 10

2 Screw EN6114V6Y14 Item 11

2 Screw ASNA2001V5-8Y Item 13

4 Screw EN6114V5Y8 Item 15

23 Nut ASNA2529-3 Item 9

2 Nut ASNA2529-6 Item 12

2 Nut NAS1726-5E Item 14

4 Nut ASNA2529-5 Item 16

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

2 Install the four upper fasteners of the Frame foot:

Refer to Fig. A-FCAAB Sheet 02

4 Screw Item (55) Retained at

removal

4 Nut NSA5057-6 Item 56

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 283

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@A300-600

SERVICE BULLETIN

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

3 Install the fasteners of the stiffener at STGR 36 H45 and H46:

Refer to Fig. A-FCAAB Sheet 04

2 Rivet ASNA2050DXJ4020 Item 19

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

4 Install the fasteners of the splice H32 to H44:

Refer to Fig. A-FCAAB Sheet 05

1 Screw EN6115V3A7 Item 8

10 Screw EN6115V3A5 Item 17

2 Screw EN6115V3A4 Item 18

13 Nut ASNA2529-3 Item 9

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

5 Do a sealant bead around the parts with:

Polysulfide Sealant

- Fuel Tank Fillet

06ABB1 As required

(d) Install the Gussets at Frame 41, LH side.

Refer to Fig. A-FLAAB

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 284

5

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

SERVICE BULLETIN

In accordance with SRM 51-40-20, SRM 51-40-00 and SRM 51-40-30

Refer to AMM 20-21-12, Page Block 001

1 Put the gussets in position as shown on Fig. A-FLAAB Sheet 02 and Fig. AFLAAB Sheet 03.

1 Gusset Item (120) Retained at

removal

1 Gusset Item (122) Retained at

removal

NOTE: Between the Frame foot and the aft gusset, the distance must

be 2 times the thickness of the gusset.

NOTE: Between the Frame foot and the FWD gusset, the distance

must be 1.3 times the thickness of the gusset.

2 Drill holes H24 and H25 to the diameter given on Fig. A-FLAAB Sheet 03.

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

4 Install:

1 Gusset Item (120) Retained at

removal

1 Gusset Item (122) Retained at

removal

2 Screw EN6114V6Y14 Item 11

1 Screw EN6114V4Y9 Item 20

1 Screw EN6114V4Y10 Item 22

2 Nut ASNA2529-6 Item 12

2 Nut ASNA2529-4 Item 21

(5) Subtask 536177-831-005-001 - Depending on Inspection results, if removed, install

the Fasteners at FR41, LH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 41

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 285

5

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

SERVICE BULLETIN

Manpower Resources

Manhours 6.00

Minimum number of person 2

Subtask elapsed time 3.00

Skills AIRFRAME

Material necessary to do the job

Component COMPA01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

9 ASNA2529-3 32 NUT

90 ASNA2019-56-25 32 RIVET

91 EN6114V3X5 32 SCREW

92 EN6080D6X-32 20 RIVET

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

NOTE: The components listed above are only necessary if crack is found on a

Frame foot. The quantity of these items are to be ordered as required.

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant - Fuel

Tank Brushable

06ABA1 As required

References

Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001

Structural Repair Manual (SRM) 51-24-00

51-40-00

51-40-20

51-40-30

Fig. A-FVAAA

Removal/Installation of the Fasteners

from FR41 to FR46, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

(a) If removed, install the fasteners at Frame 41, LH side.

Refer to Fig. A-FVAAA

In accordance with SRM 51-40-20, SRM 51-24-00, SRM 51-40-00 and SRM

51-40-30

Refer to AMM 20-21-12, Page Block 001

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 286

5

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

SERVICE BULLETIN

1 Install:

20 Rivet EN6080D6X-32 Item 92

And:

32 Rivet ASNA2019-56-25 Item 90

or

32 Screw EN6114V3X5 Item 91

32 Nut ASNA2529-3 Item 9

NOTE: Protect the fasteners with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

(6) Subtask 536177-831-006-001 - Depending on Inspection results, if necessary,

remove the Fasteners from FR41, RH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 41

Manpower Resources

Manhours 4.00

Minimum number of person 2

Subtask elapsed time 2.00

Skills AIRFRAME

References

Structural Repair Manual (SRM) 51-40-20

Fig. A-FVAAA

Removal/Installation of the Fasteners

from FR41 to FR46, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

(a) If necessary, to ease the replacement of the Frame foot, remove fasteners from

Frame 41, RH side.

Refer to Fig. A-FVAAA

In accordance with SRM 51-40-20

1 Remove:

20 Rivet Item (19) Discard

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 287

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@A300-600

SERVICE BULLETIN

And:

32 Rivet Item (5) Discard

or

32 Bolt Item (3) Discard

32 Nut Item (4) Discard

(7) Subtask 536177-831-007-002 - Depending on Inspection results, remove the

Gussets from FR41, RH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 41

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills AIRFRAME

References

Structural Repair Manual (SRM) 51-40-20

Fig. A-FLAAB

Removal/Installation of the Gussets at

FR41, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

(a) Remove the Gussets from Frame 41, RH side.

Refer to Fig. A-FLAAB

In accordance with SRM 51-40-20

1 Remove:

1 Gusset Item (121) Retain

1 Gusset Item (123) Retain

attached with:

2 Pin Item (1) Discard

2 Collar Item (2) Discard

2 Screw Item (3) Discard

2 Nut Item (4) Discard

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 288

5

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

SERVICE BULLETIN

(8) Subtask 536177-831-008-002 - Depending on Inspection results, remove the Frame

Foot from FR41, RH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 41

Manpower Resources

Manhours 16.00

Minimum number of person 2

Subtask elapsed time 8.00

Skills AIRFRAME

References

Structural Repair Manual (SRM) 51-40-20

Fig. A-FCAAB

Replacement of the Frame foot FR41,

LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

(a) Remove the Frame foot from Frame 41, RH side.

Refer to Fig. A-FCAAB

In accordance with SRM 51-40-20

1 Remove:

1 Frame foot Item (101) Discard

1 Stiffener Item (57) Retain

1 Splice Item (59) Retain

1 Shim Item (61) Retain

4 Screw Item (55) Retain

4 Nut Item (56) Discard

42 Pin Item (1) Discard

42 Collar Item (2) Discard

2 Screw Item (3) Discard

2 Nut Item (4) Discard

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 289

5

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

SERVICE BULLETIN

2 Rivet Item (5) Discard

(9) Subtask 536177-831-009-002 - Depending on Inspection results, install an identical

Frame Foot at FR41, RH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 41

Manpower Resources

Manhours 16.00

Minimum number of person 2

Subtask elapsed time 8.00

Skills AIRFRAME

Material necessary to do the job

Kit 536177A20R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

8 EN6115V3A7 15 SCREW

9 ASNA2529-3 36 NUT

10 EN6115V3A6 9 SCREW

11 EN6114V6Y14 4 SCREW

12 ASNA2529-6 4 NUT

13 ASNA2001V5-8Y 2 SCREW

14 NAS1726-5E 2 NUT

15 EN6114V5Y8 4 SCREW

16 ASNA2529-5 4 NUT

17 EN6115V3A5 10 SCREW

18 EN6115V3A4 2 SCREW

19 ASNA2050DXJ4020 2 RIVET

20 EN6114V4Y9 1 SCREW

21 ASNA2529-4 2 NUT

22 EN6114V4Y10 1 SCREW

56 NSA5057-6 4 NUT

101 A5711112920195 1 FOOT

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Wash Primer - Structure 04CMA2 As required

Primer Polyurethane Paint -

Corrosion Inhibiting

04EAC2 As required

Polysulfide Sealant -

General Purpose Brushable

06AAA1 As required

Polysulfide Sealant - Fuel

Tank Brushable

06ABA1 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 290

5

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

SERVICE BULLETIN

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant - Fuel

Tank Fillet

06ABB1 As required

References

Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001

Structural Repair Manual (SRM) 51-40-00

51-40-20

51-40-30

51-40-40

Fig. A-FCAAB

Replacement of the Frame foot FR41,

LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Fig. A-FLAAB

Removal/Installation of the Gussets at

FR41, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

(a) Install and drill all the parts.

Refer to Fig. A-FCAAB

In accordance with SRM 51-40-40

1 Put all the parts in position as shown on Fig. A-FCAAB.

1 Frame foot A5711112920195 Item 101

1 Stiffener Item (57) Retained at

removal

1 Splice Item (59) Retained at

removal

1 Shim Item (61) Retained at

removal

NOTE: If necessary, rework the upper and side surfaces of the Frame

foot with a maximum of 0.5 mm (0.020 in.) as shown on Fig.

A-FCAAB Sheet 03.

NOTE: Between parts apply:

Polysulfide Sealant

- Fuel Tank Fillet

06ABB1 As required

2 Drill the holes of the Frame foot H1 to H23 and H26 to H31 to the diameter

given on Fig. A-FCAAB Sheet 03 and Fig. A-FCAAB Sheet 04.

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 291

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@A300-600

SERVICE BULLETIN

3 Drill the holes of the stiffener H45 and H46 to the diameter given on Fig. AFCAAB Sheet 04.

4 Drill the holes of the splice H32 to H44 to the diameter given on Fig. A-FCAAB

Sheet 05.

(b) Cut-out the Frame foot Item 100 as shown on Fig. A-FCAAB Sheet 03.

Protect the cut-out with:

Wash Primer -

Structure

04CMA2 As required

Primer

Polyurethane Paint

- Corrosion

Inhibiting

04EAC2 As required

(c) Install the fasteners.

Refer to Fig. A-FCAAB

In accordance with SRM 51-40-00, SRM 51-40-20 and SRM 51-40-30

Refer to AMM 20-21-12, Page Block 001

1 Install the fasteners of the Frame foot H1 to H31:

Refer to Fig. A-FCAAB Sheet 03 and Fig. A-FCAAB Sheet 04

14 Screw EN6115V3A7 Item 8

9 Screw EN6115V3A6 Item 10

2 Screw EN6114V6Y14 Item 11

2 Screw ASNA2001V5-8Y Item 13

4 Screw EN6114V5Y8 Item 15

23 Nut ASNA2529-3 Item 9

2 Nut ASNA2529-6 Item 12

2 Nut NAS1726-5E Item 14

4 Nut ASNA2529-5 Item 16

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 292

5

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

SERVICE BULLETIN

2 Install the four upper fasteners of the Frame foot:

Refer to Fig. A-FCAAB Sheet 02

4 Screw Item (55) Retained at

removal

4 Nut NSA5057-6 Item 56

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

3 Install the fasteners of the stiffener at STGR 36 H45 and H46:

Refer to Fig. A-FCAAB Sheet 04

2 Rivet ASNA2050DXJ4020 Item 19

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

4 Install the fasteners of the splice H32 to H44:

Refer to Fig. A-FCAAB Sheet 05

1 Screw EN6115V3A7 Item 8

10 Screw EN6115V3A5 Item 17

2 Screw EN6115V3A4 Item 18

13 Nut ASNA2529-3 Item 9

NOTE: Wet install the fasteners with:

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 293

5

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

SERVICE BULLETIN

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

5 Do a sealant bead around the parts with:

Polysulfide Sealant

- Fuel Tank Fillet

06ABB1 As required

(d) Install the Gussets at Frame 41, LH side.

Refer to Fig. A-FLAAB

In accordance with SRM 51-40-20, SRM 51-40-00 and SRM 51-40-30

Refer to AMM 20-21-12, Page Block 001

1 Put the gussets in position as shown on Fig. A-FLAAB Sheet 02 and Fig. AFLAAB Sheet 03.

1 Gusset Item (121) Retained at

removal

1 Gusset Item (123) Retained at

removal

NOTE: Between the Frame foot and the aft gusset, the distance must

be 2 times the thickness of the gusset.

NOTE: Between the Frame foot and the FWD gusset, the distance

must be 1.3 times the thickness of the gusset.

2 Drill holes H24 and H25 to the diameter given on Fig. A-FLAAB Sheet 03.

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

4 Install:

1 Gusset Item (121) Retained at

removal

1 Gusset Item (123) Retained at

removal

2 Screw EN6114V6Y14 Item 11

1 Screw EN6114V4Y9 Item 20

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 294

5

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

SERVICE BULLETIN

1 Screw EN6114V4Y10 Item 22

2 Nut ASNA2529-6 Item 12

2 Nut ASNA2529-4 Item 21

(10) Subtask 536177-831-010-001 - Depending on Inspection results, if removed, install

the Fasteners at FR41, RH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 41

Manpower Resources

Manhours 6.00

Minimum number of person 2

Subtask elapsed time 3.00

Skills AIRFRAME

Material necessary to do the job

Component COMPA01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

9 ASNA2529-3 32 NUT

90 ASNA2019-56-25 32 RIVET

91 EN6114V3X5 32 SCREW

92 EN6080D6X-32 20 RIVET

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

NOTE: The components listed above are only necessary if crack is found on a

Frame foot. The quantity of these items are to be ordered as required.

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant - Fuel

Tank Brushable

06ABA1 As required

References

Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001

Structural Repair Manual (SRM) 51-24-00

51-40-00

51-40-20

51-40-30

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 295

5

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

SERVICE BULLETIN

References

Fig. A-FVAAA

Removal/Installation of the Fasteners

from FR41 to FR46, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

(a) If removed, install the fasteners at Frame 41, RH side.

Refer to Fig. A-FVAAA

In accordance with SRM 51-40-20, SRM 51-24-00, SRM 51-40-00 and SRM

51-40-30

Refer to AMM 20-21-12, Page Block 001

1 Install:

20 Rivet EN6080D6X-32 Item 92

And:

32 Rivet ASNA2019-56-25 Item 90

or

32 Screw EN6114V3X5 Item 91

32 Nut ASNA2529-3 Item 9

NOTE: Protect the fasteners with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

(11) Subtask 536177-831-011-001 - Depending on Inspection results, if necessary,

remove the Fasteners from FR42, LH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 42

Manpower Resources

Manhours 4.00

Minimum number of person 2

Subtask elapsed time 2.00

Skills AIRFRAME

References

Structural Repair Manual (SRM) 51-40-20

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 296

5

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

SERVICE BULLETIN

References

Fig. A-FVAAA

Removal/Installation of the Fasteners

from FR41 to FR46, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

(a) If necessary, to ease the replacement of the Frame foot, remove fasteners from

Frame 42, LH side.

Refer to Fig. A-FVAAA

In accordance with SRM 51-40-20

1 Remove:

16 Rivet Item (19) Discard

And:

24 Rivet Item (5) Discard

or

24 Bolt Item (3) Discard

24 Nut Item (4) Discard

(12) Subtask 536177-831-012-002 - Depending on Inspection results, remove the

Gussets from FR42, LH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 42

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills AIRFRAME

References

Structural Repair Manual (SRM) 51-40-20

Fig. A-FNAAB

Removal/Installation of the Gussets at

FR42, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

(a) Remove the Gussets from Frame 42, LH side.

Refer to Fig. A-FNAAB

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 297

5

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

SERVICE BULLETIN

In accordance with SRM 51-40-20

1 Remove:

1 Gusset Item (124) Retain

1 Gusset Item (126) Retain

attached with:

2 Pin Item (1) Discard

2 Collar Item (2) Discard

2 Screw Item (3) Discard

2 Nut Item (4) Discard

(13) Subtask 536177-831-013-002 - Depending on Inspection results, remove the Frame

Foot from FR42, LH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 42

Manpower Resources

Manhours 16.00

Minimum number of person 2

Subtask elapsed time 8.00

Skills AIRFRAME

References

Structural Repair Manual (SRM) 51-40-20

Fig. A-FDAAB

Replacement of the Frame foot FR42,

LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

(a) Remove the Frame foot from Frame 42, LH side.

Refer to Fig. A-FDAAB

In accordance with SRM 51-40-20

1 Remove:

1 Frame foot Item (102) Discard

1 Doubler Item (62) Retain

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 298

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@A300-600

SERVICE BULLETIN

1 Shim Item (63) Retain

1 Shim Item (64) Retain

1 Shim Item (65) Retain

1 Stiffener Item (58) Retain

1 Stiffener Item (68) Retain

1 Splice Item (66) Retain

4 Screw Item (55) Retain

4 Nut Item (56) Discard

46 Pin Item (1) Discard

46 Collar Item (2) Discard

15 Screw Item (3) Discard

15 Nut Item (4) Discard

6 Rivet Item (5) Discard

(14) Subtask 536177-831-014-002 - Depending on Inspection results, install an identical

Frame Foot at FR42, LH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 42

Manpower Resources

Manhours 16.00

Minimum number of person 2

Subtask elapsed time 8.00

Skills AIRFRAME

Material necessary to do the job

Kit 536177A05R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

8 EN6115V3A7 1 SCREW

9 ASNA2529-3 53 NUT

10 EN6115V3A6 11 SCREW

12 ASNA2529-6 2 NUT

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 299

5

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

SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

13 ASNA2001V5-8Y 2 SCREW

14 NAS1726-5E 2 NUT

15 EN6114V5Y8 8 SCREW

16 ASNA2529-5 8 NUT

17 EN6115V3A5 10 SCREW

18 EN6115V3A4 4 SCREW

19 ASNA2050DXJ4020 4 RIVET

20 EN6114V4Y9 1 SCREW

21 ASNA2529-4 2 NUT

22 EN6114V4Y10 1 SCREW

32 EN6115V3A8 14 SCREW

33 EN6115V3A9 11 SCREW

34 EN6114V6Y13 2 SCREW

56 NSA5057-6 4 NUT

102 A5711113020095 1 FOOT

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Wash Primer - Structure 04CMA2 As required

Primer Polyurethane Paint -

Corrosion Inhibiting

04EAC2 As required

Polysulfide Sealant -

General Purpose Brushable

06AAA1 As required

Polysulfide Sealant - Fuel

Tank Brushable

06ABA1 As required

Polysulfide Sealant - Fuel

Tank Fillet

06ABB1 As required

References

Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001

Structural Repair Manual (SRM) 51-40-00

51-40-20

51-40-30

51-40-40

Fig. A-FDAAB

Replacement of the Frame foot FR42,

LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Fig. A-FNAAB

Removal/Installation of the Gussets at

FR42, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

(a) Install and drill all the parts.

Refer to Fig. A-FDAAB

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 300

5

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

SERVICE BULLETIN

In accordance with SRM 51-40-40

1 Put all the parts in position as shown on Fig. A-FDAAB

1 Frame foot A5711113020095 Item 102

1 Doubler Item (62) Retained at

removal

1 Shim Item (63) Retained at

removal

1 Shim Item (64) Retained at

removal

1 Shim Item (65) Retained at

removal

1 Splice Item (66) Retained at

removal

1 Stiffener Item (58) Retained at

removal

1 Stiffener Item (68) Retained at

removal

NOTE: If necessary, rework the upper and side surfaces of the Frame

foot with a maximum of 0.5 mm (0.020 in.) as shown on Fig.

A-FDAAB Sheet 03.

NOTE: Between parts apply:

Polysulfide Sealant

- Fuel Tank Fillet

06ABB1 As required

2 Drill the holes of the Frame foot H51 to H78, H83 to H90 and H93 to H102 to

the diameter given on Fig. A-FDAAB Sheet 03 to Fig. A-FDAAB Sheet 05.

3 Drill the holes of the stiffener at STGR 37 H81, H82, H103 and H104 to the

diameter given on Fig. A-FDAAB Sheet 05.

4 Drill the holes of the splice H105 to H117 to the diameter given on Fig. AFDAAB Sheet 05.

(b) Cut-out the Frame foot Item 102 as shown on Fig. A-FDAAB Sheet 03.

Protect the cut-out with:

Wash Primer -

Structure

04CMA2 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 301

5

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

SERVICE BULLETIN

Primer

Polyurethane Paint

- Corrosion

Inhibiting

04EAC2 As required

(c) Install the fasteners.

Refer to Fig. A-FDAAB

In accordance with SRM 51-40-00, SRM 51-40-20 and SRM 51-40-30

Refer to AMM 20-21-12, Page Block 001

1 Install the fasteners of the Frame foot H51 to H78, H83 to H90 and H93 to

H102:

Refer to Fig. A-FDAAB Sheet 03 and Fig. A-FDAAB Sheet 04

11 Screw EN6115V3A6 Item 10

2 Screw ASNA2001V5-8Y Item 13

8 Screw EN6114V5Y8 Item 15

14 Screw EN6115V3A8 Item 32

11 Screw EN6115V3A9 Item 33

36 Nut ASNA2529-3 Item 9

2 Nut NAS1726-5E Item 14

8 Nut ASNA2529-5 Item 16

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

2 Install the four upper fasteners of the Frame foot:

Refer to Fig. A-FDAAB Sheet 02

4 Screw Item (55) Retained at

removal

4 Nut NSA5057-6 Item 56

NOTE: Wet install the fasteners with:

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 302

5

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

SERVICE BULLETIN

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

3 Install the fasteners of the stiffener at STGR 36 H79 and H80:

Refer to Fig. A-FDAAB Sheet 04

2 Rivet ASNA2050DXJ4020 Item 19

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

4 Install the fasteners of the stiffener at STGR 37 H81, H82, H103 and H104:

Refer to Fig. A-FDAAB Sheet 05

2 Screw EN6115V3A4 Item 18

2 Nut ASNA2529-3 Item 9

2 Rivet ASNA2050DXJ4020 Item 19

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

5 Install the fasteners of the splice H105 to H117:

Refer to Fig. A-FDAAB Sheet 05

1 Screw EN6115V3A7 Item 8

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 303

5

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

SERVICE BULLETIN

10 Screw EN6115V3A5 Item 17

2 Screw EN6115V3A4 Item 18

15 Nut ASNA2529-3 Item 9

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

6 Do a sealant bead around the parts with:

Polysulfide Sealant

- Fuel Tank Fillet

06ABB1 As required

(d) Install the Gussets at Frame 42, LH side.

Refer to Fig. A-FNAAB

In accordance with SRM 51-40-20, SRM 51-40-00, SRM 51-40-30 and SRM

51-40-40

Refer to AMM 20-21-12, Page Block 001

1 Put the gussets in position as shown on Fig. A-FNAAB.

1 Gusset Item (124) Retained at

removal

1 Gusset Item (126) Retained at

removal

NOTE: Between the Frame foot and the aft gusset, the distance must

be 2 times the thickness of the gusset.

NOTE: Between the Frame foot and the FWD gusset, the distance

must be 1.3 times the thickness of the gusset.

2 Drill holes H91 and H92 to the diameter given on Fig. A-FNAAB Sheet 03.

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

4 Install:

1 Gusset Item (124) Retained at

removal

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 304

5

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

SERVICE BULLETIN

1 Gusset Item (126) Retained at

removal

1 Screw EN6114V4Y9 Item 20

1 Screw EN6114V4Y10 Item 22

2 Screw EN6114V6Y13 Item 34

2 Nut ASNA2529-6 Item 12

2 Nut ASNA2529-4 Item 21

(15) Subtask 536177-831-015-001 - Depending on Inspection results, if removed, install

the Fasteners at FR42, LH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 42

Manpower Resources

Manhours 6.00

Minimum number of person 2

Subtask elapsed time 3.00

Skills AIRFRAME

Material necessary to do the job

Component COMPA02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

9 ASNA2529-3 24 NUT

90 ASNA2019-56-25 24 RIVET

91 EN6114V3X5 24 SCREW

92 EN6080D6X-32 16 RIVET

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

NOTE: The components listed above are only necessary if crack is found on a

Frame foot. The quantity of these items are to be ordered as required.

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant - Fuel

Tank Brushable

06ABA1 As required

References

Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 305

5

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

SERVICE BULLETIN

References

Structural Repair Manual (SRM) 51-24-00

51-40-00

51-40-20

51-40-30

Fig. A-FVAAA

Removal/Installation of the Fasteners

from FR41 to FR46, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

(a) If removed, install the fasteners at Frame 42, LH side.

Refer to Fig. A-FVAAA

In accordance with SRM 51-40-20, SRM 51-24-00, SRM 51-40-00 and SRM

51-40-30

Refer to AMM 20-21-12, Page Block 001

1 Install:

16 Rivet EN6080D6X-32 Item 92

And:

24 Rivet ASNA2019-56-25 Item 90

or

24 Screw EN6114V3X5 Item 91

24 Nut ASNA2529-3 Item 9

NOTE: Protect the fasteners with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

(16) Subtask 536177-831-016-001 - Depending on Inspection results, if necessary,

remove the Fasteners from FR42, RH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 42

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 306

5

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

SERVICE BULLETIN

Manpower Resources

Manhours 4.00

Minimum number of person 2

Subtask elapsed time 2.00

Skills AIRFRAME

References

Structural Repair Manual (SRM) 51-40-20

Fig. A-FVAAA

Removal/Installation of the Fasteners

from FR41 to FR46, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

(a) If necessary, to ease the replacement of the Frame foot, remove fasteners from

Frame 42, RH side.

Refer to Fig. A-FVAAA

In accordance with SRM 51-40-20

1 Remove:

16 Rivet Item (19) Discard

And:

24 Rivet Item (5) Discard

or

24 Bolt Item (3) Discard

24 Nut Item (4) Discard

(17) Subtask 536177-831-017-002 - Depending on Inspection results, remove the

Gussets from FR42, RH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 42

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills AIRFRAME

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 307

5

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

SERVICE BULLETIN

References

Structural Repair Manual (SRM) 51-40-20

Fig. A-FNAAB

Removal/Installation of the Gussets at

FR42, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

(a) Remove the Gussets from Frame 42, RH side.

Refer to Fig. A-FNAAB

In accordance with SRM 51-40-20

1 Remove:

1 Gusset Item (125) Retain

1 Gusset Item (127) Retain

attached with:

2 Pin Item (1) Discard

2 Collar Item (2) Discard

2 Screw Item (3) Discard

2 Nut Item (4) Discard

(18) Subtask 536177-831-018-002 - Depending on Inspection results, remove the Frame

Foot from FR42, RH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 42

Manpower Resources

Manhours 16.00

Minimum number of person 2

Subtask elapsed time 8.00

Skills AIRFRAME

References

Structural Repair Manual (SRM) 51-40-20

Fig. A-FDAAB

Replacement of the Frame foot FR42,

LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 308

5

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

SERVICE BULLETIN

(a) Remove the Frame foot from Frame 42, RH side.

Refer to Fig. A-FDAAB

In accordance with SRM 51-40-20

1 Remove:

1 Frame foot Item (103) Discard

1 Doubler Item (62) Retain

1 Shim Item (63) Retain

1 Shim Item (64) Retain

1 Shim Item (65) Retain

1 Stiffener Item (57) Retain

1 Stiffener Item (69) Retain

1 Splice Item (67) Retain

4 Screw Item (55) Retain

4 Nut Item (56) Discard

46 Pin Item (1) Discard

46 Collar Item (2) Discard

15 Screw Item (3) Discard

15 Nut Item (4) Discard

6 Rivet Item (5) Discard

(19) Subtask 536177-831-019-002 - Depending on Inspection results, install an identical

Frame Foot at FR42, RH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 42

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 309

5

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

SERVICE BULLETIN

Manpower Resources

Manhours 16.00

Minimum number of person 2

Subtask elapsed time 8.00

Skills AIRFRAME

Material necessary to do the job

Kit 536177A23R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

8 EN6115V3A7 1 SCREW

9 ASNA2529-3 53 NUT

10 EN6115V3A6 11 SCREW

12 ASNA2529-6 2 NUT

13 ASNA2001V5-8Y 2 SCREW

14 NAS1726-5E 2 NUT

15 EN6114V5Y8 8 SCREW

16 ASNA2529-5 8 NUT

17 EN6115V3A5 10 SCREW

18 EN6115V3A4 4 SCREW

19 ASNA2050DXJ4020 4 RIVET

20 EN6114V4Y9 1 SCREW

21 ASNA2529-4 2 NUT

22 EN6114V4Y10 1 SCREW

32 EN6115V3A8 14 SCREW

33 EN6115V3A9 11 SCREW

34 EN6114V6Y13 2 SCREW

56 NSA5057-6 4 NUT

103 A5711113020195 1 FOOT

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Wash Primer - Structure 04CMA2 As required

Primer Polyurethane Paint -

Corrosion Inhibiting

04EAC2 As required

Polysulfide Sealant -

General Purpose Brushable

06AAA1 As required

Polysulfide Sealant - Fuel

Tank Brushable

06ABA1 As required

Polysulfide Sealant - Fuel

Tank Fillet

06ABB1 As required

References

Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 310

5

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

SERVICE BULLETIN

References

Structural Repair Manual (SRM) 51-40-00

51-40-20

51-40-30

51-40-40

Fig. A-FDAAB

Replacement of the Frame foot FR42,

LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Fig. A-FNAAB

Removal/Installation of the Gussets at

FR42, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

(a) Install and drill all the parts.

Refer to Fig. A-FDAAB

In accordance with SRM 51-40-40

1 Put all the parts in position as shown on Fig. A-FDAAB

1 Frame foot A5711113020195 Item 103

1 Doubler Item (62) Retained at

removal

1 Shim Item (63) Retained at

removal

1 Shim Item (64) Retained at

removal

1 Shim Item (65) Retained at

removal

1 Splice Item (67) Retained at

removal

1 Stiffener Item (57) Retained at

removal

1 Stiffener Item (69) Retained at

removal

NOTE: If necessary, rework the upper and side surfaces of the Frame

foot with a maximum of 0.5 mm (0.020 in.) as shown on Fig.

A-FDAAB Sheet 03.

NOTE: Between parts apply:

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 311

5

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

SERVICE BULLETIN

Polysulfide Sealant

- Fuel Tank Fillet

06ABB1 As required

2 Drill the holes of the Frame foot H51 to H78, H83 to H90 and H93 to H102 to

the diameter given on Fig. A-FDAAB Sheet 03 to Fig. A-FDAAB Sheet 05.

3 Drill the holes of the stiffener at STGR 37 H81, H82, H103 and H104 to the

diameter given on Fig. A-FDAAB Sheet 05.

4 Drill the holes of the splice H105 to H117 to the diameter given on Fig. AFDAAB Sheet 05.

(b) Cut-out the Frame foot Item 102 as shown on Fig. A-FDAAB Sheet 03.

Protect the cut-out with:

Wash Primer -

Structure

04CMA2 As required

Primer

Polyurethane Paint

- Corrosion

Inhibiting

04EAC2 As required

(c) Install the fasteners.

Refer to Fig. A-FDAAB

In accordance with SRM 51-40-00, SRM 51-40-20 and SRM 51-40-30

Refer to AMM 20-21-12, Page Block 001

11 Screw EN6115V3A6 Item 10

2 Screw ASNA2001V5-8Y Item 13

8 Screw EN6114V5Y8 Item 15

14 Screw EN6115V3A8 Item 32

11 Screw EN6115V3A9 Item 33

36 Nut ASNA2529-3 Item 9

2 Nut NAS1726-5E Item 14

8 Nut ASNA2529-5 Item 16

1 Install the fasteners of the Frame foot H51 to H78, H83 to H90 and H93 to

H102:

Refer to Fig. A-FDAAB Sheet 03 and Fig. A-FDAAB Sheet 04

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 312

5

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

SERVICE BULLETIN

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

2 Install the four upper fasteners of the Frame foot:

Refer to Fig. A-FDAAB Sheet 02

4 Screw Item (55) Retained at

removal

4 Nut NSA5057-6 Item 56

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

3 Install the fasteners of the stiffener at STGR 36 H79 and H80:

Refer to Fig. A-FDAAB Sheet 04

2 Rivet ASNA2050DXJ4020 Item 19

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

4 Install the fasteners of the stiffener at STGR 37 H81, H82, H103 and H104:

Refer to Fig. A-FDAAB Sheet 05

2 Screw EN6115V3A4 Item 18

2 Nut ASNA2529-3 Item 9

2 Rivet ASNA2050DXJ4020 Item 19

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 313

5

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

SERVICE BULLETIN

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

5 Install the fasteners of the splice H105 to H117:

Refer to Fig. A-FDAAB Sheet 05

1 Screw EN6115V3A7 Item 8

10 Screw EN6115V3A5 Item 17

2 Screw EN6115V3A4 Item 18

15 Nut ASNA2529-3 Item 9

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

6 Do a sealant bead around the parts with:

Polysulfide Sealant

- Fuel Tank Fillet

06ABB1 As required

(d) Install the Gussets at Frame 42, LH side.

Refer to Fig. A-FNAAB

In accordance with SRM 51-40-20, SRM 51-40-00, SRM 51-40-30 and SRM

51-40-40

Refer to AMM 20-21-12, Page Block 001

1 Put the gussets in position as shown on Fig. A-FNAAB.

1 Gusset Item (125) Retained at

removal

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 314

5

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

SERVICE BULLETIN

1 Gusset Item (127) Retained at

removal

NOTE: Between the Frame foot and the aft gusset, the distance must

be 2 times the thickness of the gusset.

NOTE: Between the Frame foot and the FWD gusset, the distance

must be 1.3 times the thickness of the gusset.

2 Drill holes H91 and H92 to the diameter given on Fig. A-FNAAB Sheet 02.

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

4 Install:

1 Gusset Item (125) Retained at

removal

1 Gusset Item (127) Retained at

removal

1 Screw EN6114V4Y9 Item 20

1 Screw EN6114V4Y10 Item 22

2 Screw EN6114V6Y13 Item 34

2 Nut ASNA2529-6 Item 12

2 Nut ASNA2529-4 Item 21

(20) Subtask 536177-831-020-001 - Depending on Inspection results, if removed, install

the Fasteners at FR42, RH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 42

Manpower Resources

Manhours 6.00

Minimum number of person 2

Subtask elapsed time 3.00

Skills AIRFRAME

Material necessary to do the job

Component COMPA02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

9 ASNA2529-3 24 NUT

90 ASNA2019-56-25 24 RIVET

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 315

5

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

SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

91 EN6114V3X5 24 SCREW

92 EN6080D6X-32 16 RIVET

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

NOTE: The components listed above are only necessary if crack is found on a

Frame foot. The quantity of these items are to be ordered as required.

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant - Fuel

Tank Brushable

06ABA1 As required

References

Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001

Structural Repair Manual (SRM) 51-24-00

51-40-00

51-40-20

51-40-30

Fig. A-FVAAA

Removal/Installation of the Fasteners

from FR41 to FR46, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

(a) If removed, install the fasteners at Frame 42, RH side.

Refer to Fig. A-FVAAA

In accordance with SRM 51-40-20, SRM 51-24-00, SRM 51-40-00 and SRM

51-40-30

Refer to AMM 20-21-12, Page Block 001

1 Install:

16 Rivet EN6080D6X-32 Item 92

And:

24 Rivet ASNA2019-56-25 Item 90

or

24 Screw EN6114V3X5 Item 91

24 Nut ASNA2529-3 Item 9

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 316

5

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

SERVICE BULLETIN

NOTE: Protect the fasteners with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

(21) Subtask 536177-831-021-001 - Depending on Inspection results, if necessary,

remove the Fasteners from FR43, LH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 43

Manpower Resources

Manhours 4.00

Minimum number of person 2

Subtask elapsed time 2.00

Skills AIRFRAME

References

Structural Repair Manual (SRM) 51-40-20

Fig. A-FVAAA

Removal/Installation of the Fasteners

from FR41 to FR46, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

(a) If necessary, to ease the replacement of the Frame foot, remove fasteners from

Frame 43, LH side.

Refer to Fig. A-FVAAA

In accordance with SRM 51-40-20

1 Remove:

16 Rivet Item (19) Discard

And:

24 Rivet Item (5) Discard

or

24 Bolt Item (3) Discard

24 Nut Item (4) Discard

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 317

5

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@A300-600

SERVICE BULLETIN

(22) Subtask 536177-831-022-002 - Depending on Inspection results, remove the

Gussets from FR43, LH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 43

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills AIRFRAME

References

Structural Repair Manual (SRM) 51-40-20

Fig. A-FPAAB

Removal/Installation of the Gussets at

FR43, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

(a) Remove the Gussets from Frame 43, LH side.

Refer to Fig. A-FPAAB

In accordance with SRM 51-40-20

1 Remove:

1 Gusset Item (128) Retain

1 Gusset Item (130) Retain

attached with:

2 Pin Item (1) Discard

2 Collar Item (2) Discard

2 Screw Item (3) Discard

2 Nut Item (4) Discard

(23) Subtask 536177-831-023-002 - Depending on Inspection results, remove the Frame

Foot from FR43, LH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 43

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 318

5

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

SERVICE BULLETIN

Manpower Resources

Manhours 16.00

Minimum number of person 2

Subtask elapsed time 8.00

Skills AIRFRAME

References

Structural Repair Manual (SRM) 51-40-20

Fig. A-FEAAB

Replacement of the Frame foot FR43,

LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

(a) Remove the Frame foot from Frame 43, LH side.

Refer to Fig. A-FEAAB

In accordance with SRM 51-40-20

1 Remove:

1 Frame foot Item (104) Discard

1 Stiffener Item (58) Retain

1 Shim Item (70) Retain

1 Splice Item (72) Retain

4 Bolt Item (55) Retain

4 Nut Item (56) Discard

45 Pin Item (1) Discard

45 Collar Item (2) Discard

2 Bolt Item (3) Discard

2 Nut Item (4) Discard

2 Rivet Item (5) Discard

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 319

5

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

SERVICE BULLETIN

(24) Subtask 536177-831-024-002 - Depending on Inspection results, install an identical

Frame Foot at FR43, LH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 43

Manpower Resources

Manhours 16.00

Minimum number of person 2

Subtask elapsed time 8.00

Skills AIRFRAME

Material necessary to do the job

Kit 536177A08R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

8 EN6115V3A7 7 SCREW

9 ASNA2529-3 39 NUT

10 EN6115V3A6 10 SCREW

11 EN6114V6Y14 2 SCREW

12 ASNA2529-6 2 NUT

13 ASNA2001V5-8Y 2 SCREW

14 NAS1726-5E 2 NUT

15 EN6114V5Y8 4 SCREW

16 ASNA2529-5 5 NUT

17 EN6115V3A5 9 SCREW

19 ASNA2050DXJ4020 2 RIVET

20 EN6114V4Y9 1 SCREW

21 ASNA2529-4 1 NUT

32 EN6115V3A8 11 SCREW

33 EN6115V3A9 1 SCREW

36 EN6115V3A3 5 SCREW

37 EN6114V5Y10 1 SCREW

56 NSA5057-6 4 NUT

104 A5711113120095 1 FOOT

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Wash Primer - Structure 04CMA2 As required

Primer Polyurethane Paint -

Corrosion Inhibiting

04EAC2 As required

Polysulfide Sealant -

General Purpose Brushable

06AAA1 As required

Polysulfide Sealant - Fuel

Tank Brushable

06ABA1 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 320

5

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

SERVICE BULLETIN

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant - Fuel

Tank Fillet

06ABB1 As required

References

Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001

Structural Repair Manual (SRM) 51-40-00

51-40-20

51-40-30

51-40-40

Fig. A-FEAAB

Replacement of the Frame foot FR43,

LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Fig. A-FPAAB

Removal/Installation of the Gussets at

FR43, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

(a) Install and drill all the parts.

Refer to Fig. A-FEAAB

In accordance with SRM 51-40-40

1 Put all the parts in position as shown on Fig. A-FEAAB.

1 Frame foot A5711113120095 Item 104

1 Stiffener Item (58) Retained at

removal

1 Shim Item (70) Retained at

removal

1 Splice Item (72) Retained at

removal

NOTE: If necessary, rework the upper and side surfaces of the Frame

foot with a maximum of 0.5 mm (0.020 in.) as shown on Fig.

A-FEAAB Sheet 03.

NOTE: Between parts apply:

Polysulfide Sealant

- Fuel Tank Fillet

06ABB1 As required

2 Drill the holes of the Frame foot H121 to H136, H140 to H149 and H152 to

H157 to the diameter given on Fig. A-FEAAB Sheet 03 and Fig. A-FEAAB

Sheet 04.

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 321

5

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

SERVICE BULLETIN

3 Drill the holes of the stiffener H168 and H169 to the diameter given on Fig. AFEAAB Sheet 04.

4 Drill the holes of the splice H137 to H139 and H158 to H167 to the diameter

given on Fig. A-FEAAB Sheet 04.

(b) Cut-out the Frame foot Item 104 as shown on Fig. A-FEAAB Sheet 03.

Protect the cut-out with:

Wash Primer -

Structure

04CMA2 As required

Primer

Polyurethane Paint

- Corrosion

Inhibiting

04EAC2 As required

(c) Install the fasteners.

Refer to Fig. A-FEAAB

In accordance with SRM 51-40-00, SRM 51-40-20 and SRM 51-40-30

Refer to AMM 20-21-12, Page Block 001

1 Install the fasteners of the Frame foot H121 to H136, H140 to H149 and H152

to H157:

Refer to Fig. A-FEAAB Sheet 03 and Fig. A-FEAAB Sheet 04

5 Screw EN6115V3A7 Item 8

10 Screw EN6115V3A6 Item 10

2 Screw ASNA2001V5-8Y Item 13

4 Screw EN6114V5Y8 Item 15

5 Screw EN6115V3A5 Item 17

5 Screw EN6115V3A8 Item 32

5 Screw EN6115V3A3 Item 36

26 Nut ASNA2529-3 Item 9

2 Nut NAS1726-5E Item 14

4 Nut ASNA2529-5 Item 16

NOTE: Wet install the fasteners with:

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 322

5

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

SERVICE BULLETIN

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

2 Install the four upper fasteners of the Frame foot:

Refer to Fig. A-FEAAB Sheet 02

4 Bolt Item (55) Retained at

removal

4 Nut NSA5057-6 Item 56

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

3 Install the fasteners of the stiffener at STGR 36 H168 and H169:

Refer to Fig. A-FEAAB Sheet 04

2 Rivet ASNA2050DXJ4020 Item 19

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

4 Install the fasteners of the splice H137 to H139 and H158 to H167:

Refer to Fig. A-FEAAB Sheet 05

2 Screw EN6115V3A7 Item 8

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 323

5

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

SERVICE BULLETIN

4 Screw EN6115V3A5 Item 17

6 Screw EN6115V3A8 Item 32

1 Screw EN6115V3A9 Item 33

13 Nut ASNA2529-3 Item 9

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

5 Do a sealant bead around the parts with:

Polysulfide Sealant

- Fuel Tank Fillet

06ABB1 As required

(d) Install the Gussets at Frame 43, LH side.

Refer to Fig. A-FPAAB

In accordance with SRM 51-40-20, SRM 51-40-00, SRM 51-40-30 and SRM

51-40-40

Refer to AMM 20-21-12, Page Block 001

1 Put the gussets in position as shown on Fig. A-FPAAB Sheet 02 and Fig. AFPAAB Sheet 03.

1 Gusset Item (128) Retained at

removal

1 Gusset Item (130) Retained at

removal

NOTE: Between the Frame foot and the aft gusset, the distance must

be 2 times the thickness of the gusset.

NOTE: Between the Frame foot and the FWD gusset, the distance

must be 1.3 times the thickness of the gusset.

2 Drill holes H150 and H151 to the diameter given on Fig. A-FPAAB Sheet 03.

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

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 324

5

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

SERVICE BULLETIN

4 Install:

1 Gusset Item (128) Retained at

removal

1 Gusset Item (130) Retained at

removal

2 Screw EN6114V6Y14 Item 11

1 Screw EN6114V4Y9 Item 20

1 Screw EN6114V5Y10 Item 37

2 Nut ASNA2529-6 Item 12

1 Nut ASNA2529-5 Item 16

1 Nut ASNA2529-4 Item 21

(25) Subtask 536177-831-025-001 - Depending on Inspection results, if removed, install

the Fasteners at FR43, LH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 43

Manpower Resources

Manhours 6.00

Minimum number of person 2

Subtask elapsed time 3.00

Skills AIRFRAME

Material necessary to do the job

Component COMPA03

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

9 ASNA2529-3 24 NUT

47 EN6114V3X6 24 SCREW

90 ASNA2019-56-25 24 RIVET

92 EN6080D6X-32 16 RIVET

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

NOTE: The components listed above are only necessary if crack is found on a

Frame foot. The quantity of these items are to be ordered as required.

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 325

5

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

SERVICE BULLETIN

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant - Fuel

Tank Brushable

06ABA1 As required

References

Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001

Structural Repair Manual (SRM) 51-24-00

51-40-00

51-40-20

51-40-30

Fig. A-FVAAA

Removal/Installation of the Fasteners

from FR41 to FR46, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

(a) If removed, install the fasteners at Frame 43, LH side.

Refer to Fig. A-FVAAA

In accordance with SRM 51-40-20, SRM 51-24-00, SRM 51-40-00 and SRM

51-40-30

Refer to AMM 20-21-12, Page Block 001

1 Install:

16 Rivet EN6080D6X-32 Item 92

And:

24 Rivet ASNA2019-56-25 Item 90

or

24 Screw EN6114V3X6 Item 47

24 Nut ASNA2529-3 Item 9

NOTE: Protect the fasteners with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 326

5

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

SERVICE BULLETIN

(26) Subtask 536177-831-026-001 - Depending on Inspection results, if necessary,

remove the Fasteners from FR43, RH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 43

Manpower Resources

Manhours 4.00

Minimum number of person 2

Subtask elapsed time 2.00

Skills AIRFRAME

References

Structural Repair Manual (SRM) 51-40-20

Fig. A-FVAAA

Removal/Installation of the Fasteners

from FR41 to FR46, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

(a) If necessary, to ease the replacement of the Frame foot, remove fasteners from

Frame 43, RH side.

Refer to Fig. A-FVAAA

In accordance with SRM 51-40-20

1 Remove:

16 Rivet Item (19) Discard

And:

24 Rivet Item (5) Discard

or

24 Bolt Item (3) Discard

24 Nut Item (4) Discard

(27) Subtask 536177-831-027-002 - Depending on Inspection results, remove the

Gussets from FR43, RH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 43

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 327

5

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

SERVICE BULLETIN

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills AIRFRAME

References

Structural Repair Manual (SRM) 51-40-20

Fig. A-FPAAB

Removal/Installation of the Gussets at

FR43, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

(a) Remove the Gussets from Frame 43, RH side.

Refer to Fig. A-FPAAB

In accordance with SRM 51-40-20

1 Remove:

1 Gusset Item (129) Retain

1 Gusset Item (131) Retain

attached with:

2 Pin Item (1) Discard

2 Collar Item (2) Discard

2 Screw Item (3) Discard

2 Nut Item (4) Discard

(28) Subtask 536177-831-028-002 - Depending on Inspection results, remove the Frame

Foot from FR43, RH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 43

Manpower Resources

Manhours 16.00

Minimum number of person 2

Subtask elapsed time 8.00

Skills AIRFRAME

References

Structural Repair Manual (SRM) 51-40-20

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 328

5

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

SERVICE BULLETIN

References

Fig. A-FEAAB

Replacement of the Frame foot FR43,

LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

(a) Remove the Frame foot from Frame 43, RH side.

Refer to Fig. A-FEAAB

In accordance with SRM 51-40-20

1 Remove:

1 Frame foot Item (105) Discard

1 Stiffener Item (57) Retain

1 Shim Item (70) Retain

1 Splice Item (71) Retain

4 Bolt Item (55) Retain

4 Nut Item (56) Discard

45 Pin Item (1) Discard

45 Collar Item (2) Discard

2 Bolt Item (3) Discard

2 Nut Item (4) Discard

2 Rivet Item (5) Discard

(29) Subtask 536177-831-029-002 - Depending on Inspection results, install an identical

Frame Foot at FR43, RH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 43

Manpower Resources

Manhours 16.00

Minimum number of person 2

Subtask elapsed time 8.00

Skills AIRFRAME

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 329

5

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

SERVICE BULLETIN

Material necessary to do the job

Kit 536177A26R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

8 EN6115V3A7 7 SCREW

9 ASNA2529-3 39 NUT

10 EN6115V3A6 10 SCREW

11 EN6114V6Y14 2 SCREW

12 ASNA2529-6 2 NUT

13 ASNA2001V5-8Y 2 SCREW

14 NAS1726-5E 2 NUT

15 EN6114V5Y8 4 SCREW

16 ASNA2529-5 5 NUT

17 EN6115V3A5 9 SCREW

19 ASNA2050DXJ4020 2 RIVET

20 EN6114V4Y9 1 SCREW

21 ASNA2529-4 1 NUT

32 EN6115V3A8 11 SCREW

33 EN6115V3A9 1 SCREW

36 EN6115V3A3 5 SCREW

37 EN6114V5Y10 1 SCREW

56 NSA5057-6 4 NUT

105 A5711113120195 1 FOOT

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Wash Primer - Structure 04CMA2 As required

Primer Polyurethane Paint -

Corrosion Inhibiting

04EAC2 As required

Polysulfide Sealant -

General Purpose Brushable

06AAA1 As required

Polysulfide Sealant - Fuel

Tank Brushable

06ABA1 As required

Polysulfide Sealant - Fuel

Tank Fillet

06ABB1 As required

References

Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001

Structural Repair Manual (SRM) 51-40-00

51-40-20

51-40-30

51-40-40

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 330

5

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

SERVICE BULLETIN

References

Fig. A-FEAAB

Replacement of the Frame foot FR43,

LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Fig. A-FPAAB

Removal/Installation of the Gussets at

FR43, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

(a) Install and drill all the parts.

Refer to Fig. A-FEAAB

In accordance with SRM 51-40-40

1 Put all the parts in position as shown on Fig. A-FEAAB.

1 Frame foot A5711113120195 Item 105

1 Stiffener Item (57) Retained at

removal

1 Shim Item (70) Retained at

removal

1 Splice Item (71) Retained at

removal

NOTE: If necessary, rework the upper and side surfaces of the Frame

foot with a maximum of 0.5 mm (0.020 in.) as shown on Fig.

A-FEAAB Sheet 03.

NOTE: Between parts apply:

Polysulfide Sealant

- Fuel Tank Fillet

06ABB1 As required

2 Drill the holes of the Frame foot H121 to H136, H140 to H149 and H152 to

H157 to the diameter given on Fig. A-FEAAB Sheet 03 and Fig. A-FEAAB

Sheet 04.

3 Drill the holes of the stiffener H168 and H169 to the diameter given on Fig. AFEAAB Sheet 04.

4 Drill the holes of the splice H137 to H139 and H158 to H167 to the diameter

given on Fig. A-FEAAB Sheet 04.

(b) Cut-out the Frame foot Item 104 as shown on Fig. A-FEAAB Sheet 03.

Protect the cut-out with:

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 331

5

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

SERVICE BULLETIN

Wash Primer -

Structure

04CMA2 As required

Primer

Polyurethane Paint

- Corrosion

Inhibiting

04EAC2 As required

(c) Install the fasteners.

Refer to Fig. A-FEAAB

In accordance with SRM 51-40-00, SRM 51-40-20 and SRM 51-40-30

Refer to AMM 20-21-12, Page Block 001

1 Install the fasteners of the Frame foot H121 to H136, H140 to H149 and H152

to H157:

Refer to Fig. A-FEAAB Sheet 03 and Fig. A-FEAAB Sheet 04

5 Screw EN6115V3A7 Item 8

10 Screw EN6115V3A6 Item 10

2 Screw ASNA2001V5-8Y Item 13

4 Screw EN6114V5Y8 Item 15

5 Screw EN6115V3A5 Item 17

5 Screw EN6115V3A8 Item 32

5 Screw EN6115V3A3 Item 36

26 Nut ASNA2529-3 Item 9

2 Nut NAS1726-5E Item 14

4 Nut ASNA2529-5 Item 16

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 332

5

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

SERVICE BULLETIN

2 Install the four upper fasteners of the Frame foot:

Refer to Fig. A-FEAAB Sheet 02

4 Bolt Item (55) Retained at

removal

4 Nut NSA5057-6 Item 56

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

3 Install the fasteners of the stiffener at STGR 36 H168 and H169:

Refer to Fig. A-FEAAB Sheet 04

2 Rivet ASNA2050DXJ4020 Item 19

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

4 Install the fasteners of the splice H137 to H139 and H158 to H167:

Refer to Fig. A-FEAAB Sheet 05

2 Screw EN6115V3A7 Item 8

4 Screw EN6115V3A5 Item 17

6 Screw EN6115V3A8 Item 32

1 Screw EN6115V3A9 Item 33

13 Nut ASNA2529-3 Item 9

NOTE: Wet install the fasteners with:

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 333

5

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

SERVICE BULLETIN

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

5 Do a sealant bead around the parts with:

Polysulfide Sealant

- Fuel Tank Fillet

06ABB1 As required

(d) Install the Gussets at Frame 43, LH side.

Refer to Fig. A-FPAAB

In accordance with SRM 51-40-20, SRM 51-40-00, SRM 51-40-30 and SRM

51-40-40

Refer to AMM 20-21-12, Page Block 001

1 Put the gussets in position as shown on Fig. A-FPAAB Sheet 02 and Fig. AFPAAB Sheet 03.

1 Gusset Item (129) Retained at

removal

1 Gusset Item (131) Retained at

removal

NOTE: Between the Frame foot and the aft gusset, the distance must

be 2 times the thickness of the gusset.

NOTE: Between the Frame foot and the FWD gusset, the distance

must be 1.3 times the thickness of the gusset.

2 Drill holes H150 and H151 to the diameter given on Fig. A-FPAAB Sheet 02.

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

4 Install:

1 Gusset Item (129) Retained at

removal

1 Gusset Item (131) Retained at

removal

2 Screw EN6114V6Y14 Item 11

1 Screw EN6114V4Y9 Item 20

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 334

5

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

SERVICE BULLETIN

1 Screw EN6114V5Y10 Item 37

2 Nut ASNA2529-6 Item 12

1 Nut ASNA2529-5 Item 16

1 Nut ASNA2529-4 Item 21

(30) Subtask 536177-831-030-001 - Depending on Inspection results, if removed, install

the Fasteners at FR43, RH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 43

Manpower Resources

Manhours 6.00

Minimum number of person 2

Subtask elapsed time 3.00

Skills AIRFRAME

Material necessary to do the job

Component COMPA03

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

9 ASNA2529-3 24 NUT

47 EN6114V3X6 24 SCREW

90 ASNA2019-56-25 24 RIVET

92 EN6080D6X-32 16 RIVET

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

NOTE: The components listed above are only necessary if crack is found on a

Frame foot. The quantity of these items are to be ordered as required.

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant - Fuel

Tank Brushable

06ABA1 As required

References

Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001

Structural Repair Manual (SRM) 51-24-00

51-40-00

51-40-20

51-40-30

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 335

5

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

SERVICE BULLETIN

References

Fig. A-FVAAA

Removal/Installation of the Fasteners

from FR41 to FR46, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

(a) If removed, install the fasteners at Frame 43, RH side.

Refer to Fig. A-FVAAA

In accordance with SRM 51-40-20, SRM 51-24-00, SRM 51-40-00 and SRM

51-40-30

Refer to AMM 20-21-12, Page Block 001

1 Install:

16 Rivet EN6080D6X-32 Item 92

And:

24 Rivet ASNA2019-56-25 Item 90

or

24 Screw EN6114V3X6 Item 47

24 Nut ASNA2529-3 Item 9

NOTE: Protect the fasteners with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

(31) Subtask 536177-831-031-001 - Depending on Inspection results, if necessary,

remove the Fasteners from FR44, LH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 44

Manpower Resources

Manhours 4.00

Minimum number of person 2

Subtask elapsed time 2.00

Skills AIRFRAME

References

Structural Repair Manual (SRM) 51-40-20

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 336

5

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

SERVICE BULLETIN

References

Fig. A-FVAAA

Removal/Installation of the Fasteners

from FR41 to FR46, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

(a) If necessary, to ease the replacement of the Frame foot, remove fasteners from

Frame 44, LH side.

Refer to Fig. A-FVAAA

In accordance with SRM 51-40-20

1 Remove:

16 Rivet Item (19) Discard

And:

24 Rivet Item (5) Discard

or

24 Bolt Item (3) Discard

24 Nut Item (4) Discard

(32) Subtask 536177-831-032-002 - Depending on Inspection results, remove the

Gussets from FR44, LH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 44

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills AIRFRAME

References

Structural Repair Manual (SRM) 51-40-20

Fig. A-FQAAB

Removal/Installation of the Gussets at

FR44, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

(a) Remove the Gussets from Frame 44, LH side.

Refer to Fig. A-FQAAB

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 337

5

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

SERVICE BULLETIN

In accordance with SRM 51-40-20

1 Remove:

1 Gusset Item (132) Retain

1 Gusset Item (134) Retain

attached with:

2 Pin Item (1) Discard

2 Collar Item (2) Discard

2 Screw Item (3) Discard

2 Nut Item (4) Discard

(33) Subtask 536177-831-033-002 - Depending on Inspection results, remove the Frame

Foot from FR44, LH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 44

Manpower Resources

Manhours 16.00

Minimum number of person 2

Subtask elapsed time 8.00

Skills AIRFRAME

References

Structural Repair Manual (SRM) 51-40-20

Fig. A-FGAAB

Replacement of the Frame foot FR44,

LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

(a) Remove the Frame foot from Frame 44, LH side.

Refer to Fig. A-FGAAB

In accordance with SRM 51-40-20

1 Remove:

1 Frame foot Item (106) Discard

1 Stiffener Item (58) Retain

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 338

5

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

SERVICE BULLETIN

1 Splice Item (74) Retain

1 Shim Item (73) Retain

4 Bolt Item (55) Retain

4 Nut Item (56) Discard

39 Pin Item (1) Discard

39 Collar Item (2) Discard

2 Bolt Item (3) Discard

2 Nut Item (4) Discard

2 Rivet Item (5) Discard

(34) Subtask 536177-831-034-002 - Depending on Inspection results, install an identical

Frame Foot at FR44, LH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 44

Manpower Resources

Manhours 16.00

Minimum number of person 2

Subtask elapsed time 8.00

Skills AIRFRAME

Material necessary to do the job

Kit 536177A11R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

8 EN6115V3A7 11 SCREW

9 ASNA2529-3 35 NUT

10 EN6115V3A6 12 SCREW

11 EN6114V6Y14 2 SCREW

12 ASNA2529-6 2 NUT

13 ASNA2001V5-8Y 2 SCREW

14 NAS1726-5E 2 NUT

15 EN6114V5Y8 2 SCREW

16 ASNA2529-5 4 NUT

17 EN6115V3A5 9 SCREW

18 EN6115V3A4 2 SCREW

19 ASNA2050DXJ4020 2 RIVET

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 339

5

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

SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

36 EN6115V3A3 1 SCREW

37 EN6114V5Y10 2 SCREW

56 NSA5057-6 4 NUT

106 A5711113220095 1 FOOT

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Wash Primer - Structure 04CMA2 As required

Primer Polyurethane Paint -

Corrosion Inhibiting

04EAC2 As required

Polysulfide Sealant -

General Purpose Brushable

06AAA1 As required

Polysulfide Sealant - Fuel

Tank Brushable

06ABA1 As required

Polysulfide Sealant - Fuel

Tank Fillet

06ABB1 As required

References

Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001

Structural Repair Manual (SRM) 51-40-00

51-40-20

51-40-30

51-40-40

Fig. A-FQAAB

Removal/Installation of the Gussets at

FR44, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Fig. A-FGAAB

Replacement of the Frame foot FR44,

LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

(a) Install and drill all the parts.

Refer to Fig. A-FGAAB

In accordance with SRM 51-40-40

1 Put all the parts in position as shown on Fig. A-FGAAB.

1 Frame foot A5711113220095 Item 106

1 Stiffener Item (58) Retained at

removal

1 Splice Item (74) Retained at

removal

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 340

5

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

SERVICE BULLETIN

1 Shim Item (73) Retained at

removal

NOTE: If necessary, rework the upper and side surfaces of the Frame

foot with a maximum of 0.5 mm (0.020 in.) as shown on Fig.

A-FGAAB Sheet 03.

NOTE: Between parts apply:

Polysulfide Sealant

- Fuel Tank Fillet

06ABB1 As required

2 Drill the holes of the Frame foot H180 to H202 and H205 to H208 to the

diameter given on Fig. A-FGAAB Sheet 03 and Fig. A-FGAAB Sheet 04.

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

4 Drill the holes of the splice H209 to H220 to the diameter given on Fig. AFGAAB Sheet 05.

(b) Cut-out the Frame foot Item 106 as shown on Fig. A-FGAAB Sheet 03.

Protect the cut-out with:

Wash Primer -

Structure

04CMA2 As required

Primer

Polyurethane Paint

- Corrosion

Inhibiting

04EAC2 As required

(c) Install the fasteners.

Refer to Fig. A-FGAAB

In accordance with SRM 51-40-00, SRM 51-40-20, and SRM 51-40-30

Refer to AMM 20-21-12, Page Block 001

1 Install the fasteners of the Frame foot H180 to H202 and H205 to H208:

Refer to Fig. A-FGAAB Sheet 03 and Fig. A-FGAAB Sheet 04

10 Screw EN6115V3A7 Item 8

12 Screw EN6115V3A6 Item 10

2 Screw ASNA2001V5-8Y Item 13

2 Screw EN6114V5Y8 Item 15

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 341

5

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

SERVICE BULLETIN

1 Screw EN6115V3A3 Item 36

23 Nut ASNA2529-3 Item 9

2 Nut NAS1726-5E Item 14

2 Nut ASNA2529-5 Item 16

NOTE: For holes H205 to H208, adjust the shims as shown on Fig. AFGAAB Sheet 04.

NOTE: Wet install the fasteners except for holes H203 and H204 with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

2 Install the four upper fasteners of the Frame foot:

Refer to Fig. A-FGAAB Sheet 02

4 Bolt Item (55) Retained at

removal

4 Nut NSA5057-6 Item 56

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

3 Install the fasteners of the stiffener at STGR 36 H221 and H222:

Refer to Fig. A-FGAAB Sheet 03

2 Rivet ASNA2050DXJ4020 Item 19

NOTE: Wet install the fasteners with:

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 342

5

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

SERVICE BULLETIN

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

4 Install the fasteners of the splice H209 to H220:

Refer to Fig. A-FGAAB Sheet 05

1 Screw EN6115V3A7 Item 8

9 Screw EN6115V3A5 Item 17

2 Screw EN6115V3A4 Item 18

12 Nut ASNA2529-3 Item 9

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

5 Do a sealant bead around the parts with:

Polysulfide Sealant

- Fuel Tank Fillet

06ABB1 As required

(d) Install the Gussets at Frame 44, LH side.

Refer to Fig. A-FQAAB

In accordance with SRM 51-40-20, SRM 51-40-00 and SRM 51-40-30

Refer to AMM 20-21-12, Page Block 001

1 Put the gussets in position as shown on Fig. A-FQAAB.

1 Gusset Item (132) Retained at

removal

1 Gusset Item (134) Retained at

removal

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 343

5

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

SERVICE BULLETIN

NOTE: Between the Frame foot and the aft gusset, the distance must

be 2 times the thickness of the gusset.

NOTE: Between the Frame foot and the FWD gusset, the distance

must be 1.3 times the thickness of the gusset.

2 Drill holes H203 and H204 to the diameter given on Fig. A-FQAAB Sheet 03.

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

4 Install:

1 Gusset Item (132) Retained at

removal

1 Gusset Item (134) Retained at

removal

2 Screw EN6114V5Y10 Item 37

2 Screw EN6114V6Y14 Item 11

2 Nut ASNA2529-6 Item 12

2 Nut ASNA2529-5 Item 16

(35) Subtask 536177-831-035-001 - Depending on Inspection results, if removed, install

the Fasteners at FR44, LH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 44

Manpower Resources

Manhours 6.00

Minimum number of person 2

Subtask elapsed time 3.00

Skills AIRFRAME

Material necessary to do the job

Component COMPA02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

9 ASNA2529-3 24 NUT

90 ASNA2019-56-25 24 RIVET

91 EN6114V3X5 24 SCREW

92 EN6080D6X-32 16 RIVET

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 344

5

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

SERVICE BULLETIN

NOTE: The components listed above are only necessary if crack is found on a

Frame foot. The quantity of these items are to be ordered as required.

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant - Fuel

Tank Brushable

06ABA1 As required

References

Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001

Structural Repair Manual (SRM) 51-24-00

51-40-00

51-40-20

51-40-30

Fig. A-FVAAA

Removal/Installation of the Fasteners

from FR41 to FR46, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

(a) If removed, install the fasteners at Frame 44, LH side.

Refer to Fig. A-FVAAA

In accordance with SRM 51-40-20, SRM 51-24-00, SRM 51-40-00 and SRM

51-40-30

Refer to AMM 20-21-12, Page Block 001

1 Install:

16 Rivet EN6080D6X-32 Item 92

And:

24 Rivet ASNA2019-56-25 Item 90

or

24 Screw EN6114V3X5 Item 91

24 Nut ASNA2529-3 Item 9

NOTE: Protect the fasteners with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 345

5

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

SERVICE BULLETIN

(36) Subtask 536177-831-036-001 - Depending on Inspection results, if necessary,

remove the Fasteners from FR44, RH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 44

Manpower Resources

Manhours 4.00

Minimum number of person 2

Subtask elapsed time 2.00

Skills AIRFRAME

References

Structural Repair Manual (SRM) 51-40-20

Fig. A-FVAAA

Removal/Installation of the Fasteners

from FR41 to FR46, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

(a) If necessary, to ease the replacement of the Frame foot, remove fasteners from

Frame 44, RH side.

Refer to Fig. A-FVAAA

In accordance with SRM 51-40-20

1 Remove:

16 Rivet Item (19) Discard

And:

24 Rivet Item (5) Discard

or

24 Bolt Item (3) Discard

24 Nut Item (4) Discard

(37) Subtask 536177-831-037-002 - Depending on Inspection results, remove the

Gussets from FR44, RH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 44

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 346

5

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

SERVICE BULLETIN

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills AIRFRAME

References

Structural Repair Manual (SRM) 51-40-20

Fig. A-FQAAB

Removal/Installation of the Gussets at

FR44, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

(a) Remove the Gussets from Frame 44, RH side.

Refer to Fig. A-FQAAB

In accordance with SRM 51-40-20

1 Remove:

1 Gusset Item (133) Retain

1 Gusset Item (135) Retain

attached with:

2 Pin Item (1) Discard

2 Collar Item (2) Discard

2 Screw Item (3) Discard

2 Nut Item (4) Discard

(38) Subtask 536177-831-038-002 - Depending on Inspection results, remove the Frame

Foot from FR44, RH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 44

Manpower Resources

Manhours 16.00

Minimum number of person 2

Subtask elapsed time 8.00

Skills AIRFRAME

References

Structural Repair Manual (SRM) 51-40-20

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 347

5

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

SERVICE BULLETIN

References

Fig. A-FGAAB

Replacement of the Frame foot FR44,

LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

(a) Remove the Frame foot from Frame 44, RH side.

Refer to Fig. A-FGAAB

In accordance with SRM 51-40-20

1 Remove:

1 Frame foot Item (107) Discard

1 Stiffener Item (57) Retain

1 Splice Item (75) Retain

1 Shim Item (73) Retain

4 Bolt Item (55) Retain

4 Nut Item (56) Discard

39 Pin Item (1) Discard

39 Collar Item (2) Discard

2 Bolt Item (3) Discard

2 Nut Item (4) Discard

2 Rivet Item (5) Discard

(39) Subtask 536177-831-039-002 - Depending on Inspection results, install an identical

Frame Foot at FR44, RH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 44

Manpower Resources

Manhours 16.00

Minimum number of person 2

Subtask elapsed time 8.00

Skills AIRFRAME

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 348

5

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

SERVICE BULLETIN

Material necessary to do the job

Kit 536177A29R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

8 EN6115V3A7 11 SCREW

9 ASNA2529-3 35 NUT

10 EN6115V3A6 12 SCREW

11 EN6114V6Y14 2 SCREW

12 ASNA2529-6 2 NUT

13 ASNA2001V5-8Y 2 SCREW

14 NAS1726-5E 2 NUT

15 EN6114V5Y8 2 SCREW

16 ASNA2529-5 4 NUT

17 EN6115V3A5 9 SCREW

18 EN6115V3A4 2 SCREW

19 ASNA2050DXJ4020 2 RIVET

36 EN6115V3A3 1 SCREW

37 EN6114V5Y10 2 SCREW

56 NSA5057-6 4 NUT

107 A5711113220195 1 FOOT

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Wash Primer - Structure 04CMA2 As required

Primer Polyurethane Paint -

Corrosion Inhibiting

04EAC2 As required

Polysulfide Sealant -

General Purpose Brushable

06AAA1 As required

Polysulfide Sealant - Fuel

Tank Brushable

06ABA1 As required

Polysulfide Sealant - Fuel

Tank Fillet

06ABB1 As required

References

Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001

Structural Repair Manual (SRM) 51-40-00

51-40-20

51-40-30

51-40-40

Fig. A-FGAAB

Replacement of the Frame foot FR44,

LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 349

5

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

SERVICE BULLETIN

References

Fig. A-FQAAB

Removal/Installation of the Gussets at

FR44, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

(a) Install and drill all the parts.

Refer to Fig. A-FGAAB

In accordance with SRM 51-40-40

1 Put all the parts in position as shown on Fig. A-FGAAB.

1 Frame foot A5711113220195 Item 107

1 Stiffener Item (57) Retained at

removal

1 Splice Item (75) Retained at

removal

1 Shim Item (73) Retained at

removal

NOTE: If necessary, rework the upper and side surfaces of the Frame

foot with a maximum of 0.5 mm (0.020 in.) as shown on Fig.

A-FGAAB Sheet 03.

NOTE: Between parts apply:

Polysulfide Sealant

- Fuel Tank Fillet

06ABB1 As required

2 Drill the holes of the Frame foot H180 to H202 and H205 to H208 to the

diameter given on Fig. A-FGAAB Sheet 03 and Fig. A-FGAAB Sheet 04.

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

4 Drill the holes of the splice H209 to H220 to the diameter given on Fig. AFGAAB Sheet 05.

(b) Cut-out the Frame foot Item 106 as shown on Fig. A-FGAAB Sheet 03.

Protect the cut-out with:

Wash Primer -

Structure

04CMA2 As required

Primer

Polyurethane Paint

- Corrosion

Inhibiting

04EAC2 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 350

5

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

SERVICE BULLETIN

(c) Install the fasteners.

Refer to Fig. A-FGAAB

In accordance with SRM 51-40-00, SRM 51-40-20, and SRM 51-40-30

Refer to AMM 20-21-12, Page Block 001

1 Install the fasteners of the Frame foot H180 to H202 and H205 to H208:

Refer to Fig. A-FGAAB Sheet 03 and Fig. A-FGAAB Sheet 04

10 Screw EN6115V3A7 Item 8

12 Screw EN6115V3A6 Item 10

2 Screw ASNA2001V5-8Y Item 13

2 Screw EN6114V5Y8 Item 15

1 Screw EN6115V3A3 Item 36

23 Nut ASNA2529-3 Item 9

2 Nut NAS1726-5E Item 14

2 Nut ASNA2529-5 Item 16

NOTE: For holes H205 to H208, adjust the shims as shown on Fig. AFGAAB Sheet 04.

NOTE: Wet install the fasteners except for holes H203 and H204 with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

2 Install the four upper fasteners of the Frame foot:

Refer to Fig. A-FGAAB Sheet 02

4 Bolt Item (55) Retained at

removal

4 Nut NSA5057-6 Item 56

NOTE: Wet install the fasteners with:

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 351

5

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

SERVICE BULLETIN

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

3 Install the fasteners of the stiffener at STGR 36 H221 and H222:

Refer to Fig. A-FGAAB Sheet 03

2 Rivet ASNA2050DXJ4020 Item 19

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

4 Install the fasteners of the splice H209 to H220:

Refer to Fig. A-FGAAB Sheet 05

1 Screw EN6115V3A7 Item 8

9 Screw EN6115V3A5 Item 17

2 Screw EN6115V3A4 Item 18

12 Nut ASNA2529-3 Item 9

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 352

5

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

SERVICE BULLETIN

5 Do a sealant bead around the parts with:

Polysulfide Sealant

- Fuel Tank Fillet

06ABB1 As required

(d) Install the Gussets at Frame 44, LH side.

Refer to Fig. A-FQAAB

In accordance with SRM 51-40-20, SRM 51-40-00 and SRM 51-40-30

Refer to AMM 20-21-12, Page Block 001

1 Put the gussets in position as shown on Fig. A-FQAAB.

1 Gusset Item (133) Retained at

removal

1 Gusset Item (135) Retained at

removal

NOTE: Between the Frame foot and the aft gusset, the distance must

be 2 times the thickness of the gusset.

NOTE: Between the Frame foot and the FWD gusset, the distance

must be 1.3 times the thickness of the gusset.

2 Drill holes H203 and H204 to the diameter given on Fig. A-FQAAB Sheet 03.

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

4 Install:

1 Gusset Item (133) Retained at

removal

1 Gusset Item (135) Retained at

removal

2 Screw EN6114V5Y10 Item 37

2 Screw EN6114V6Y14 Item 11

2 Nut ASNA2529-6 Item 12

2 Nut ASNA2529-5 Item 16

(40) Subtask 536177-831-040-001 - Depending on Inspection results, if removed, install

the Fasteners at FR44, RH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 44

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 353

5

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

SERVICE BULLETIN

Manpower Resources

Manhours 6.00

Minimum number of person 2

Subtask elapsed time 3.00

Skills AIRFRAME

Material necessary to do the job

Component COMPA02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

9 ASNA2529-3 24 NUT

90 ASNA2019-56-25 24 RIVET

91 EN6114V3X5 24 SCREW

92 EN6080D6X-32 16 RIVET

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

NOTE: The components listed above are only necessary if crack is found on a

Frame foot. The quantity of these items are to be ordered as required.

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant - Fuel

Tank Brushable

06ABA1 As required

References

Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001

Structural Repair Manual (SRM) 51-24-00

51-40-00

51-40-20

51-40-30

Fig. A-FVAAA

Removal/Installation of the Fasteners

from FR41 to FR46, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

(a) If removed, install the fasteners at Frame 44, RH side.

Refer to Fig. A-FVAAA

In accordance with SRM 51-40-20, SRM 51-24-00, SRM 51-40-00 and SRM

51-40-30

Refer to AMM 20-21-12, Page Block 001

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 354

5

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

SERVICE BULLETIN

1 Install:

16 Rivet EN6080D6X-32 Item 92

And:

24 Rivet ASNA2019-56-25 Item 90

or

24 Screw EN6114V3X5 Item 91

24 Nut ASNA2529-3 Item 9

NOTE: Protect the fasteners with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

(41) Subtask 536177-831-041-001 - Depending on Inspection results, if necessary,

remove the Fasteners from FR45, LH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 45

Manpower Resources

Manhours 4.00

Minimum number of person 2

Subtask elapsed time 2.00

Skills AIRFRAME

References

Structural Repair Manual (SRM) 51-40-20

Fig. A-FVAAA

Removal/Installation of the Fasteners

from FR41 to FR46, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

(a) If necessary, to ease the replacement of the Frame foot, remove fasteners from

Frame 45, LH side.

Refer to Fig. A-FVAAA

In accordance with SRM 51-40-20

1 Remove:

20 Rivet Item (19) Discard

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 355

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@A300-600

SERVICE BULLETIN

And:

32 Rivet Item (5) Discard

or

32 Bolt Item (3) Discard

32 Nut Item (4) Discard

(42) Subtask 536177-831-042-002 - Depending on Inspection results, remove the

Gussets from FR45, LH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 45

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills AIRFRAME

References

Structural Repair Manual (SRM) 51-40-20

Fig. A-FTAAB

Removal/Installation of the Gussets at

FR45, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

(a) Remove the Gussets from Frame 45, LH side.

Refer to Fig. A-FTAAB

In accordance with SRM 51-40-20

1 Remove:

1 Gusset Item (136) Retain

1 Gusset Item (138) Retain

attached with:

2 Pin Item (1) Discard

2 Collar Item (2) Discard

2 Screw Item (3) Discard

2 Nut Item (4) Discard

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 356

5

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

SERVICE BULLETIN

(43) Subtask 536177-831-043-002 - Depending on Inspection results, remove the Frame

Foot from FR45, LH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 45

Manpower Resources

Manhours 16.00

Minimum number of person 2

Subtask elapsed time 8.00

Skills AIRFRAME

References

Structural Repair Manual (SRM) 51-40-20

Fig. A-FJAAB

Replacement of the Frame foot FR45,

LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

(a) Remove the Frame foot from Frame 45, LH side.

Refer to Fig. A-FJAAB

In accordance with SRM 51-40-20

1 Remove:

1 Frame foot Item (108) Discard

2 Stiffener Item (58) Retain

1 Splice Item (72) Retain

1 Doubler Item (77) Retain

1 Shim Item (78) Retain

36 Pin Item (1) Discard

36 Collar Item (2) Discard

4 Rivet Item (19) Discard

15 Screw Item (3) Discard

15 Nut Item (4) Discard

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 357

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

SERVICE BULLETIN

And:

4 Screw Item (55) Retain

4 Nut Item (56) Discard

or

4 Nut Item (76) Discard

And:

1 Rivet Item (5) Discard

or

1 Screw Item (93) Discard

1 Nut Item (94) Discard

And if installed, remove:

1 Bracket Item (79) Retain

(44) Subtask 536177-831-044-002 - Depending on Inspection results, install an identical

Frame Foot at FR45, LH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 145

Manpower Resources

Manhours 16.00

Minimum number of person 2

Subtask elapsed time 8.00

Skills AIRFRAME

Material necessary to do the job

Kit 536177A14R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

8 EN6115V3A7 4 SCREW

9 ASNA2529-3 48 NUT

10 EN6115V3A6 7 SCREW

11 EN6114V6Y14 2 SCREW

12 ASNA2529-6 2 NUT

16 ASNA2529-5 2 NUT

17 EN6115V3A5 3 SCREW

19 ASNA2050DXJ4020 4 RIVET

32 EN6115V3A8 7 SCREW

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 358

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

SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

33 EN6115V3A9 17 SCREW

37 EN6114V5Y10 2 SCREW

42 EN6114V3A6 1 SCREW

43 EN6115V3A10 2 SCREW

44 EN6115V3A11 7 SCREW

45 ASNA2001V6-8Y 2 SCREW

46 NAS1726-6E 2 NUT

56 NSA5057-6 4 NUT

76 NSA5057-7 4 NUT

108 A5711113320095 1 FOOT

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Wash Primer - Structure 04CMA2 As required

Primer Polyurethane Paint -

Corrosion Inhibiting

04EAC2 As required

Polysulfide Sealant -

General Purpose Brushable

06AAA1 As required

Polysulfide Sealant - Fuel

Tank Brushable

06ABA1 As required

Polysulfide Sealant - Fuel

Tank Fillet

06ABB1 As required

References

Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001

Structural Repair Manual (SRM) 51-40-00

51-40-20

51-40-30

51-40-40

Fig. A-FJAAB

Replacement of the Frame foot FR45,

LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Fig. A-FTAAB

Removal/Installation of the Gussets at

FR45, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

(a) Install and drill all the parts.

Refer to Fig. A-FJAAB

In accordance with SRM 51-40-40

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 359

5

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

SERVICE BULLETIN

1 Put all the parts in position as shown on Fig. A-FJAAB.

1 Frame foot A5711113320095 Item 108

2 Stiffener Item (58) Retained at

removal

1 Splice Item (72) Retained at

removal

1 Doubler Item (77) Retained at

removal

1 Shim Item (78) Retained at

removal

NOTE: If necessary, rework the upper and side surfaces of the Frame

foot with a maximum of 0.5 mm (0.020 in.) as shown on Fig.

A-FJAAB Sheet 03.

NOTE: Between parts apply:

Polysulfide Sealant

- Fuel Tank Fillet

06ABB1 As required

2 Drill the holes of the Frame foot H231 to H254, H257 to H266 and H271 to

H272 to the diameter given on Fig. A-FJAAB Sheet 03 to Fig. A-FJAAB Sheet

05.

3 Drill the holes of the stiffener at STGR 36 H255 and H256 to the diameter

given on Fig. A-FJAAB Sheet 03.

4 Drill the holes of the stiffener at STGR 37 H267 and H268 to the diameter

given on Fig. A-FJAAB Sheet 05.

5 Drill the holes of the splice H273 to H285 to the diameter given on Fig. AFJAAB Sheet 06.

(b) Cut-out the Frame foot Item 108 as shown on Fig. A-FJAAB Sheet 03.

Protect the cut-out with:

Wash Primer -

Structure

04CMA2 As required

Primer

Polyurethane Paint

- Corrosion

Inhibiting

04EAC2 As required

(c) Install the fasteners.

Refer to Fig. A-FJAAB

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 360

5

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

SERVICE BULLETIN

In accordance with SRM 51-40-00, SRM 51-40-20 and SRM 51-40-30

Refer to AMM 20-21-12, Page Block 001

1 Install the fasteners of the Frame foot H231 to H254, H257 to H266 and H271

to H272:

Refer to Fig. A-FJAAB Sheet 03 to Fig. A-FJAAB Sheet 05

2 Screw EN6115V3A7 Item 8

5 Screw EN6115V3A6 Item 10

1 Screw EN6115V3A5 Item 17

1 Screw EN6115V3A8 Item 32

16 Screw EN6115V3A9 Item 33

1 Screw EN6114V3A6 Item 42

2 Screw EN6115V3A10 Item 43

7 Screw EN6115V3A11 Item 44

2 Screw ASNA2001V6-8Y Item 45

35 Nut ASNA2529-3 Item 9

2 Nut NAS1726-6E Item 46

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

2 Install the four upper fasteners of the Frame foot:

Refer to Fig. A-FJAAB Sheet 02

4 Bolt Item (55) Retained at

removal

4 Nut NSA5057-6 Item 56

or

4 Nut NSA5057-7 Item 76

NOTE: Wet install the fasteners with:

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 361

5

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

SERVICE BULLETIN

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

3 Install the fasteners of the stiffener at STGR 36 H255 and H256:

Refer to Fig. A-FJAAB Sheet 03

2 Rivet ASNA2050DXJ4020 Item 19

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

4 Install the fasteners of the stiffener at STGR 37 H267 and H268:

Refer to Fig. A-FJAAB Sheet 06

2 Rivet ASNA2050DXJ4020 Item 19

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

5 Install the fasteners of the splice H273 to H285:

Refer to Fig. A-FJAAB Sheet 06

2 Screw EN6115V3A7 Item 8

2 Screw EN6115V3A5 Item 17

6 Screw EN6115V3A8 Item 32

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 362

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

SERVICE BULLETIN

1 Screw EN6115V3A9 Item 33

13 Nut ASNA2529-3 Item 9

2 Screw EN6115V3A6 Item 10

And if removed, install:

1 Bracket Item (79) Retained at

removal

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

6 Do a sealant bead around the parts with:

Polysulfide Sealant

- Fuel Tank Fillet

06ABB1 As required

(d) Install the Gussets at Frame 45, LH side.

Refer to Fig. A-FTAAB

In accordance with SRM 51-40-20, SRM 51-40-00, SRM 51-40-30 and SRM

51-40-40

Refer to AMM 20-21-12, Page Block 001

1 Put the gussets in position as shown on Fig. A-FTAAB.

1 Gusset Item (136) Retained at

removal

1 Gusset Item (138) Retained at

removal

NOTE: Between the Frame foot and the aft gusset, the distance must

be 2 times the thickness of the gusset.

NOTE: Between the Frame foot and the FWD gusset, the distance

must be 1.3 times the thickness of the gusset.

2 Drill holes H269 and H270 to the diameter given on Fig. A-FTAAB Sheet 02.

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

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 363

5

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

SERVICE BULLETIN

4 Install:

1 Gusset Item (136) Retained at

removal

1 Gusset Item (138) Retained at

removal

2 Screw EN6114V6Y14 Item 11

2 Screw EN6114V5Y10 Item 37

2 Nut ASNA2529-6 Item 12

2 Nut ASNA2529-5 Item 16

(45) Subtask 536177-831-045-001 - Depending on Inspection results, if removed, install

the Fasteners at FR45, LH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 45

Manpower Resources

Manhours 6.00

Minimum number of person 2

Subtask elapsed time 3.00

Skills AIRFRAME

Material necessary to do the job

Component COMPA04

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

9 ASNA2529-3 32 NUT

47 EN6114V3X6 32 SCREW

90 ASNA2019-56-25 32 RIVET

92 EN6080D6X-32 20 RIVET

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

NOTE: The components listed above are only necessary if crack is found on a

Frame foot. The quantity of these items are to be ordered as required.

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant - Fuel

Tank Brushable

06ABA1 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 364

5

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

SERVICE BULLETIN

References

Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001

Structural Repair Manual (SRM) 51-24-00

51-40-00

51-40-20

51-40-30

Fig. A-FVAAA

Removal/Installation of the Fasteners

from FR41 to FR46, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

(a) If removed, install the fasteners at Frame 45, LH side.

Refer to Fig. A-FVAAA

In accordance with SRM 51-40-20, SRM 51-24-00, SRM 51-40-00 and SRM

51-40-30

Refer to AMM 20-21-12, Page Block 001

1 Install:

20 Rivet EN6080D6X-32 Item 92

And:

32 Rivet ASNA2019-56-25 Item 90

or

32 Screw EN6114V3X6 Item 47

32 Nut ASNA2529-3 Item 9

NOTE: Protect the fasteners with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

(46) Subtask 536177-831-046-001 - Depending on Inspection results, if necessary,

remove the Fasteners from FR45, RH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 45

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 365

5

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

SERVICE BULLETIN

Manpower Resources

Manhours 4.00

Minimum number of person 2

Subtask elapsed time 2.00

Skills AIRFRAME

References

Structural Repair Manual (SRM) 51-40-20

Fig. A-FVAAA

Removal/Installation of the Fasteners

from FR41 to FR46, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

(a) If necessary, to ease the replacement of the Frame foot, remove fasteners from

Frame 45, RH side.

Refer to Fig. A-FVAAA

In accordance with SRM 51-40-20

1 Remove:

20 Rivet Item (19) Discard

And:

32 Rivet Item (5) Discard

or

32 Bolt Item (3) Discard

32 Nut Item (4) Discard

(47) Subtask 536177-831-047-002 - Depending on Inspection results, remove the

Gussets from FR45, RH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 45

Manpower Resources

Manhours 1.00

Minimum number of person 2

Subtask elapsed time 1.00

Skills AIRFRAME

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 366

5

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

SERVICE BULLETIN

References

Structural Repair Manual (SRM) 51-40-20

Fig. A-FTAAB

Removal/Installation of the Gussets at

FR45, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

(a) Remove the Gussets from Frame 45, RH side.

Refer to Fig. A-FTAAB

In accordance with SRM 51-40-20

1 Remove:

1 Gusset Item (137) Retain

1 Gusset Item (139) Retain

attached with:

2 Pin Item (1) Discard

2 Collar Item (2) Discard

2 Screw Item (3) Discard

2 Nut Item (4) Discard

(48) Subtask 536177-831-048-002 - Depending on Inspection results, remove the Frame

Foot from FR45, RH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 45

Manpower Resources

Manhours 16.00

Minimum number of person 2

Subtask elapsed time 8.00

Skills AIRFRAME

References

Structural Repair Manual (SRM) 51-40-20

Fig. A-FJAAB

Replacement of the Frame foot FR45,

LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 367

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@A300-600

SERVICE BULLETIN

(a) Remove the Frame foot from Frame 45, RH side.

Refer to Fig. A-FJAAB

In accordance with SRM 51-40-20

1 Remove:

1 Frame foot Item (109) Discard

2 Stiffener Item (57) Retain

1 Splice Item (71) Retain

1 Doubler Item (77) Retain

1 Shim Item (78) Retain

36 Pin Item (1) Discard

36 Collar Item (2) Discard

4 Rivet Item (19) Discard

15 Screw Item (3) Discard

15 Nut Item (4) Discard

And:

4 Screw Item (55) Retain

4 Nut Item (56) Discard

or

4 Nut Item (76) Discard

And:

1 Rivet Item (5) Discard

or

1 Screw Item (93) Discard

1 Nut Item (94) Discard

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 368

5

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

SERVICE BULLETIN

(49) Subtask 536177-831-049-002 - Depending on Inspection results, install an identical

Frame Foot at FR45, RH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 45

Manpower Resources

Manhours 16.00

Minimum number of person 2

Subtask elapsed time 8.00

Skills AIRFRAME

Material necessary to do the job

Kit 536177A32R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

8 EN6115V3A7 4 SCREW

9 ASNA2529-3 48 NUT

10 EN6115V3A6 5 SCREW

11 EN6114V6Y14 2 SCREW

12 ASNA2529-6 2 NUT

16 ASNA2529-5 2 NUT

17 EN6115V3A5 5 SCREW

19 ASNA2050DXJ4020 4 RIVET

32 EN6115V3A8 7 SCREW

33 EN6115V3A9 17 SCREW

37 EN6114V5Y10 2 SCREW

42 EN6114V3A6 1 SCREW

43 EN6115V3A10 2 SCREW

44 EN6115V3A11 7 SCREW

45 ASNA2001V6-8Y 2 SCREW

46 NAS1726-6E 2 NUT

56 NSA5057-6 4 NUT

76 NSA5057-7 4 NUT

109 A5711113320195 1 FOOT

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Wash Primer - Structure 04CMA2 As required

Primer Polyurethane Paint -

Corrosion Inhibiting

04EAC2 As required

Polysulfide Sealant -

General Purpose Brushable

06AAA1 As required

Polysulfide Sealant - Fuel

Tank Brushable

06ABA1 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 369

5

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

SERVICE BULLETIN

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant - Fuel

Tank Fillet

06ABB1 As required

References

Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001

Structural Repair Manual (SRM) 51-40-00

51-40-20

51-40-30

51-40-40

Fig. A-FJAAB

Replacement of the Frame foot FR45,

LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Fig. A-FTAAB

Removal/Installation of the Gussets at

FR45, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

(a) Install and drill all the parts.

Refer to Fig. A-FJAAB

In accordance with SRM 51-40-40

1 Put all the parts in position as shown on Fig. A-FJAAB.

1 Frame foot A5711113320195 Item 109

2 Stiffener Item (57) Retained at

removal

1 Splice Item (71) Retained at

removal

1 Doubler Item (77) Retained at

removal

1 Shim Item (78) Retained at

removal

NOTE: If necessary, rework the upper and side surfaces of the Frame

foot with a maximum of 0.5 mm (0.020 in.) as shown on Fig.

A-FJAAB Sheet 03.

NOTE: Between parts apply:

Polysulfide Sealant

- Fuel Tank Fillet

06ABB1 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 370

5

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

SERVICE BULLETIN

2 Drill the holes of the Frame foot H231 to H254, H257 to H266 and H271 to

H272 to the diameter given on Fig. A-FJAAB Sheet 03 to Fig. A-FJAAB Sheet

05.

3 Drill the holes of the stiffener at STGR 36 H255 and H256 to the diameter

given on Fig. A-FJAAB Sheet 03.

4 Drill the holes of the stiffener at STGR 37 H267 and H268 to the diameter

given on Fig. A-FJAAB Sheet 05.

5 Drill the holes of the splice H273 to H285 to the diameter given on Fig. AFJAAB Sheet 06.

(b) Cut-out the Frame foot Item 108 as shown on Fig. A-FJAAB Sheet 03.

Protect the cut-out with:

Wash Primer -

Structure

04CMA2 As required

Primer

Polyurethane Paint

- Corrosion

Inhibiting

04EAC2 As required

(c) Install the fasteners.

Refer to Fig. A-FJAAB

In accordance with SRM 51-40-00, SRM 51-40-20 and SRM 51-40-30

Refer to AMM 20-21-12, Page Block 001

1 Install the fasteners of the Frame foot H231 to H254, H257 to H266 and H271

to H272:

Refer to Fig. A-FJAAB Sheet 03 to Fig. A-FJAAB Sheet 05

2 Screw EN6115V3A7 Item 8

5 Screw EN6115V3A6 Item 10

1 Screw EN6115V3A5 Item 17

1 Screw EN6115V3A8 Item 32

16 Screw EN6115V3A9 Item 33

1 Screw EN6114V3A6 Item 42

2 Screw EN6115V3A10 Item 43

7 Screw EN6115V3A11 Item 44

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 371

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@A300-600

SERVICE BULLETIN

2 Screw ASNA2001V6-8Y Item 45

35 Nut ASNA2529-3 Item 9

2 Nut NAS1726-6E Item 46

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

2 Install the four upper fasteners of the Frame foot:

Refer to Fig. A-FJAAB Sheet 02

4 Bolt Item (55) Retained at

removal

4 Nut NSA5057-6 Item 56

or

4 Nut NSA5057-7 Item 76

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

3 Install the fasteners of the stiffener at STGR 36 H255 and H256:

Refer to Fig. A-FJAAB Sheet 03

2 Rivet ASNA2050DXJ4020 Item 19

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 372

5

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

SERVICE BULLETIN

4 Install the fasteners of the stiffener at STGR 37 H267 and H268:

Refer to Fig. A-FJAAB Sheet 06

2 Rivet ASNA2050DXJ4020 Item 19

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

5 Install the fasteners of the splice H273 to H285:

Refer to Fig. A-FJAAB Sheet 06

2 Screw EN6115V3A7 Item 8

4 Screw EN6115V3A5 Item 17

6 Screw EN6115V3A8 Item 32

1 Screw EN6115V3A9 Item 33

13 Nut ASNA2529-3 Item 9

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

6 Do a sealant bead around the parts with:

Polysulfide Sealant

- Fuel Tank Fillet

06ABB1 As required

(d) Install the Gussets at Frame 45, LH side.

Refer to Fig. A-FTAAB

In accordance with SRM 51-40-20, SRM 51-40-00, SRM 51-40-30 and SRM

51-40-40

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 373

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

SERVICE BULLETIN

Refer to AMM 20-21-12, Page Block 001

1 Put the gussets in position as shown on Fig. A-FTAAB.

1 Gusset Item (137) Retained at

removal

1 Gusset Item (139) Retained at

removal

NOTE: Between the Frame foot and the aft gusset, the distance must

be 2 times the thickness of the gusset.

NOTE: Between the Frame foot and the FWD gusset, the distance

must be 1.3 times the thickness of the gusset.

2 Drill holes H269 and H270 to the diameter given on Fig. A-FTAAB Sheet 03.

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

4 Install:

1 Gusset Item (137) Retained at

removal

1 Gusset Item (139) Retained at

removal

2 Screw EN6114V6Y14 Item 11

2 Screw EN6114V5Y10 Item 37

2 Nut ASNA2529-6 Item 12

2 Nut ASNA2529-5 Item 16

(50) Subtask 536177-831-050-001 - Depending on Inspection results, install the

Fasteners at FR45, RH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 45

Manpower Resources

Manhours 6.00

Minimum number of person 2

Subtask elapsed time 3.00

Skills AIRFRAME

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 374

5

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

SERVICE BULLETIN

Material necessary to do the job

Component COMPA04

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

9 ASNA2529-3 32 NUT

47 EN6114V3X6 32 SCREW

90 ASNA2019-56-25 32 RIVET

92 EN6080D6X-32 20 RIVET

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

NOTE: The components listed above are only necessary if crack is found on a

Frame foot. The quantity of these items are to be ordered as required.

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant - Fuel

Tank Brushable

06ABA1 As required

References

Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001

Structural Repair Manual (SRM) 51-24-00

51-40-00

51-40-20

51-40-30

Fig. A-FVAAA

Removal/Installation of the Fasteners

from FR41 to FR46, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

(a) If removed, install the fasteners at Frame 45, RH side.

Refer to Fig. A-FVAAA

In accordance with SRM 51-40-20, SRM 51-24-00, SRM 51-40-00 and SRM

51-40-30

Refer to AMM 20-21-12, Page Block 001

1 Install:

20 Rivet EN6080D6X-32 Item 92

And:

32 Rivet ASNA2019-56-25 Item 90

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 375

5

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

SERVICE BULLETIN

or

32 Screw EN6114V3X6 Item 47

32 Nut ASNA2529-3 Item 9

NOTE: Protect the fasteners with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

(51) Subtask 536177-831-051-001 - Depending on Inspection results, if necessary,

remove the Fasteners from FR46, LH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 46

Manpower Resources

Manhours 4.00

Minimum number of person 2

Subtask elapsed time 2.00

Skills AIRFRAME

References

Structural Repair Manual (SRM) 51-40-20

Fig. A-FVAAA

Removal/Installation of the Fasteners

from FR41 to FR46, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

(a) If necessary, to ease the replacement of the Frame foot, remove fasteners from

Frame 46, LH side.

Refer to Fig. A-FVAAA

In accordance with SRM 51-40-20

1 Remove:

16 Rivet Item (19) Discard

And:

24 Rivet Item (5) Discard

or

24 Bolt Item (3) Discard

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 376

5

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

SERVICE BULLETIN

24 Nut Item (4) Discard

(52) Subtask 536177-831-052-002 - Depending on Inspection results, remove the

Gussets from FR46, LH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 46

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills AIRFRAME

References

Structural Repair Manual (SRM) 51-40-20

Fig. A-FUAAB

Removal/Installation of the Gussets at

FR46, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

(a) Remove the Gussets from Frame 46, LH side.

Refer to Fig. A-FUAAB

In accordance with SRM 51-40-20

1 Remove:

1 Gusset Item (140) Retain

1 Gusset Item (142) Retain

attached with:

2 Pin Item (1) Discard

2 Collar Item (2) Discard

2 Screw Item (3) Discard

2 Nut Item (4) Discard

(53) Subtask 536177-831-053-002 - Depending on Inspection results, remove the Frame

Foot from FR46, LH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 46

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 377

5

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

SERVICE BULLETIN

Manpower Resources

Manhours 16.00

Minimum number of person 2

Subtask elapsed time 8.00

Skills AIRFRAME

References

Structural Repair Manual (SRM) 51-40-20

Fig. A-FKAAB

Replacement of the Frame foot FR46,

LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

(a) Remove the Frame foot from Frame 46, LH side.

Refer to Fig. A-FKAAB

In accordance with SRM 51-40-20

1 Remove:

1 Frame foot Item (110) Discard

1 Stiffener Item (58) Retain

1 Doubler Item (80) Retain

1 Shim Item (81) Retain

1 Splice Item (82) Retain

40 Pin Item (1) Discard

40 Collar Item (2) Discard

2 Rivet Item (19) Discard

13 Screw Item (3) Discard

13 Nut Item (4) Discard

And:

4 Screw Item (55) Retain

4 Nut Item (56) Discard

or

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 378

5

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

SERVICE BULLETIN

4 Nut Item (76) Discard

(54) Subtask 536177-831-054-002 - Depending on Inspection results, install an identical

Frame Foot at FR46, LH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 46

Manpower Resources

Manhours 16.00

Minimum number of person 1

Subtask elapsed time 8.00

Skills AIRFRAME

Material necessary to do the job

Kit 536177A17R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

8 EN6115V3A7 3 SCREW

9 ASNA2529-3 43 NUT

10 EN6115V3A6 11 SCREW

11 EN6114V6Y14 1 SCREW

12 ASNA2529-6 3 NUT

14 NAS1726-5E 2 NUT

15 EN6114V5Y8 6 SCREW

16 ASNA2529-5 7 NUT

17 EN6115V3A5 7 SCREW

18 EN6115V3A4 2 SCREW

19 ASNA2050DXJ4020 2 RIVET

33 EN6115V3A9 9 SCREW

43 EN6115V3A10 5 SCREW

44 EN6115V3A11 6 SCREW

49 EN6114V6Y17 2 SCREW

50 ASNA2001V5-12Y 2 SCREW

51 EN6114V5Y12 1 SCREW

56 NSA5057-6 4 NUT

76 NSA5057-7 4 NUT

110 A5711113420095 1 FOOT

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Wash Primer - Structure 04CMA2 As required

Primer Polyurethane Paint -

Corrosion Inhibiting

04EAC2 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 379

5

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

SERVICE BULLETIN

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant -

General Purpose Brushable

06AAA1 As required

Polysulfide Sealant - Fuel

Tank Brushable

06ABA1 As required

Polysulfide Sealant - Fuel

Tank Fillet

06ABB1 As required

References

Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001

Structural Repair Manual (SRM) 51-40-00

51-40-20

51-40-30

51-40-40

Fig. A-FKAAB

Replacement of the Frame foot FR46,

LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Fig. A-FUAAB

Removal/Installation of the Gussets at

FR46, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

(a) Install and drill all the parts.

Refer to Fig. A-FKAAB

In accordance with SRM 51-40-40

1 Put all the parts in position as shown on Fig. A-FKAAB.

1 Frame foot A5711113420095 Item 110

1 Stiffener Item (58) Retained at

removal

1 Doubler Item (80) Retained at

removal

1 Shim Item (81) Retained at

removal

1 Splice Item (82) Retained at

removal

NOTE: If necessary, rework the upper and side surfaces of the Frame

foot with a maximum of 0.5 mm (0.020 in.) as shown on Fig.

A-FKAAB Sheet 03.

NOTE: Between parts apply:

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 380

5

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

SERVICE BULLETIN

Polysulfide Sealant

- Fuel Tank Fillet

06ABB1 As required

2 Drill the holes of the Frame foot H300 to H313, H316 to H331 and H334 to

H341 to the diameter given on Fig. A-FKAAB Sheet 03 and Fig. A-FKAAB

Sheet 04.

3 Drill the holes of the stiffener H314 and H315 to the diameter given on Fig. AFKAAB Sheet 04.

4 Drill the holes of the splice H342 to H354 to the diameter given on Fig. AFKAAB Sheet 05.

(b) Cut-out the Frame foot Item 110 as shown on Fig. A-FKAAB Sheet 03.

Protect the cut-out with:

Wash Primer -

Structure

04CMA2 As required

Primer

Polyurethane Paint

- Corrosion

Inhibiting

04EAC2 As required

(c) Install the fasteners.

Refer to Fig. A-FKAAB

In accordance with SRM 51-40-00, SRM 51-40-20 and SRM 51-40-30

Refer to AMM 20-21-12, Page Block 001

1 Install the fasteners of the Frame foot H300 to H313, H316 to H331 and H334

to H341 to H313 and H316 to H341:

Refer to Fig. A-FKAAB Sheet 03 and Fig. A-FKAAB Sheet 04

2 Screw EN6115V3A7 Item 8

8 Screw EN6115V3A6 Item 10

6 Screw EN6114V5Y8 Item 15

9 Screw EN6115V3A9 Item 33

5 Screw EN6115V3A10 Item 43

6 Screw EN6115V3A11 Item 44

2 Screw ASNA2001V5-12Y Item 50

30 Nut ASNA2529-3 Item 9

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 381

5

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

SERVICE BULLETIN

2 Nut NAS1726-5E Item 14

6 Nut ASNA2529-5 Item 16

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

2 Install the four upper fasteners of the Frame foot:

Refer to Fig. A-FKAAB Sheet 02

4 Bolt Item (55) Retained at

removal

4 Nut NSA5057-6 Item 56

or

4 Nut NSA5057-7 Item 76

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

3 Install the fasteners of the stiffener at STGR 37 H314 and H315:

Refer to Fig. A-FKAAB Sheet 04

2 Rivet ASNA2050DXJ4020 Item 19

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 382

5

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

SERVICE BULLETIN

4 Install the fasteners of the splice H342 to H354:

Refer to Fig. A-FKAAB Sheet 05

1 Screw EN6115V3A7 Item 8

3 Screw EN6115V3A6 Item 10

7 Screw EN6115V3A5 Item 17

2 Screw EN6115V3A4 Item 18

13 Nut ASNA2529-3 Item 9

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

5 Do a sealant bead around the parts with:

Polysulfide Sealant

- Fuel Tank Fillet

06ABB1 As required

(d) Install the Gussets at Frame 46, LH side.

Refer to Fig. A-FUAAB

In accordance with SRM 51-40-20, SRM 51-40-00, SRM 51-40-30 and SRM

51-40-40

Refer to AMM 20-21-12, Page Block 001

1 Put the gussets in position as shown on Fig. A-FUAAB.

1 Gusset Item (140) Retained at

removal

1 Gusset Item (142) Retained at

removal

NOTE: Between the Frame foot and the aft gusset, the distance must

be 2 times the thickness of the gusset.

NOTE: Between the Frame foot and the FWD gusset, the distance

must be 1.3 times the thickness of the gusset.

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 383

5

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

SERVICE BULLETIN

2 Drill holes H332 and H333 to the diameter given on Fig. A-FUAAB Sheet 02.

3 Drill holes H355 and H356 to the diameter given on Fig. A-FUAAB Sheet 03.

4 Install:

1 Gusset Item (140) Retained at

removal

1 Gusset Item (142) Retained at

removal

1 Screw EN6114V6Y14 Item 11

2 Screw EN6114V6Y17 Item 49

1 Screw EN6114V5Y12 Item 51

3 Nut ASNA2529-6 Item 12

1 Nut ASNA2529-5 Item 16

(55) Subtask 536177-831-055-001 - Depending on Inspection results, if removed, install

the Fasteners at FR46, LH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 46

Manpower Resources

Manhours 6.00

Minimum number of person 2

Subtask elapsed time 3.00

Skills AIRFRAME

Material necessary to do the job

Component COMPA05

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

9 ASNA2529-3 24 NUT

47 EN6114V3X6 16 SCREW

90 ASNA2019-56-25 24 RIVET

91 EN6114V3X5 8 SCREW

92 EN6080D6X-32 16 RIVET

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

NOTE: The components listed above are only necessary if crack is found on a

Frame foot. The quantity of these items are to be ordered as required.

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 384

5

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

SERVICE BULLETIN

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant - Fuel

Tank Brushable

06ABA1 As required

References

Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001

Structural Repair Manual (SRM) 51-24-00

51-40-00

51-40-20

51-40-30

Fig. A-FVAAA

Removal/Installation of the Fasteners

from FR41 to FR46, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

(a) If removed, install the fasteners at Frame 46, LH side.

Refer to Fig. A-FVAAA

In accordance with SRM 51-40-20, SRM 51-24-00, SRM 51-40-00 and SRM

51-40-30

Refer to AMM 20-21-12, Page Block 001

1 Install:

16 Rivet EN6080D6X-32 Item 92

And:

16 Rivet ASNA2019-56-25 Item 90

or

16 Screw EN6114V3X6 Item 47

16 Nut ASNA2529-3 Item 9

And:

8 Rivet ASNA2019-56-25 Item 90

or

8 Screw EN6114V3X5 Item 91

8 Nut ASNA2529-3 Item 9

NOTE: Protect the fasteners with:

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 385

5

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

SERVICE BULLETIN

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

(56) Subtask 536177-831-056-001 - Depending on Inspection results, if necessary,

remove the Fasteners from FR46, RH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 46

Manpower Resources

Manhours 4.00

Minimum number of person 2

Subtask elapsed time 2.00

Skills AIRFRAME

References

Structural Repair Manual (SRM) 51-40-20

Fig. A-FVAAA

Removal/Installation of the Fasteners

from FR41 to FR46, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

(a) If necessary, to ease the replacement of the Frame foot, remove fasteners from

Frame 46, RH side.

Refer to Fig. A-FVAAA

In accordance with SRM 51-40-20

1 Remove:

16 Rivet Item (19) Discard

And:

24 Rivet Item (5) Discard

or

24 Bolt Item (3) Discard

24 Nut Item (4) Discard

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 386

5

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

SERVICE BULLETIN

(57) Subtask 536177-831-057-002 - Depending on Inspection results, remove the

Gussets from FR46, RH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 46

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills AIRFRAME

References

Structural Repair Manual (SRM) 51-40-20

Fig. A-FUAAB

Removal/Installation of the Gussets at

FR46, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

(a) Remove the Gussets from Frame 46, RH side.

Refer to Fig. A-FUAAB

In accordance with SRM 51-40-20

1 Remove:

1 Gusset Item (141) Retain

1 Gusset Item (143) Retain

attached with:

2 Pin Item (1) Discard

2 Collar Item (2) Discard

2 Screw Item (3) Discard

2 Nut Item (4) Discard

(58) Subtask 536177-831-058-002 - Depending on Inspection results, remove the Frame

Foot from FR46, RH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 46

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 387

5

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

SERVICE BULLETIN

Manpower Resources

Manhours 16.00

Minimum number of person 2

Subtask elapsed time 8.00

Skills AIRFRAME

References

Structural Repair Manual (SRM) 51-40-20

Fig. A-FKAAB

Replacement of the Frame foot FR46,

LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

(a) Remove the Frame foot from Frame 46, RH side.

Refer to Fig. A-FKAAB

In accordance with SRM 51-40-20

1 Remove:

1 Frame foot Item (111) Discard

1 Stiffener Item (57) Retain

1 Doubler Item (80) Retain

1 Shim Item (81) Retain

1 Splice Item (83) Retain

40 Pin Item (1) Discard

40 Collar Item (2) Discard

2 Rivet Item (19) Discard

13 Screw Item (3) Discard

13 Nut Item (4) Discard

And:

4 Screw Item (55) Retain

4 Nut Item (56) Discard

or

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 388

5

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

SERVICE BULLETIN

4 Nut Item (76) Discard

(59) Subtask 536177-831-059-002 - Depending on Inspection results, install an identical

Frame Foot at FR46, RH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 46

Manpower Resources

Manhours 16.00

Minimum number of person 2

Subtask elapsed time 8.00

Skills AIRFRAME

Material necessary to do the job

Kit 536177A35R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

8 EN6115V3A7 3 SCREW

9 ASNA2529-3 43 NUT

10 EN6115V3A6 8 SCREW

11 EN6114V6Y14 1 SCREW

12 ASNA2529-6 3 NUT

14 NAS1726-5E 2 NUT

15 EN6114V5Y8 6 SCREW

16 ASNA2529-5 7 NUT

17 EN6115V3A5 7 SCREW

18 EN6115V3A4 2 SCREW

19 ASNA2050DXJ4020 2 RIVET

33 EN6115V3A9 9 SCREW

43 EN6115V3A10 5 SCREW

44 EN6115V3A11 6 SCREW

49 EN6114V6Y17 2 SCREW

50 ASNA2001V5-12Y 2 SCREW

51 EN6114V5Y12 1 SCREW

56 NSA5057-6 4 NUT

76 NSA5057-7 4 NUT

111 A5711113420195 1 FOOT

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Wash Primer - Structure 04CMA2 As required

Primer Polyurethane Paint -

Corrosion Inhibiting

04EAC2 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 389

5

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

SERVICE BULLETIN

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant -

General Purpose Brushable

06AAA1 As required

Polysulfide Sealant - Fuel

Tank Brushable

06ABA1 As required

Polysulfide Sealant - Fuel

Tank Fillet

06ABB1 As required

References

Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001

Structural Repair Manual (SRM) 51-40-00

51-40-20

51-40-30

51-40-40

Fig. A-FKAAB

Replacement of the Frame foot FR46,

LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Fig. A-FUAAB

Removal/Installation of the Gussets at

FR46, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

(a) Install and drill all the parts.

Refer to Fig. A-FKAAB

In accordance with SRM 51-40-40

1 Put all the parts in position as shown on Fig. A-FKAAB.

1 Frame foot A5711113420195 Item 111

1 Stiffener Item (57) Retained at

removal

1 Doubler Item (80) Retained at

removal

1 Shim Item (81) Retained at

removal

1 Splice Item (83) Retained at

removal

NOTE: If necessary, rework the upper and side surfaces of the Frame

foot with a maximum of 0.5 mm (0.020 in.) as shown on Fig.

A-FKAAB Sheet 03.

NOTE: Between parts apply:

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 390

5

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

SERVICE BULLETIN

Polysulfide Sealant

- Fuel Tank Fillet

06ABB1 As required

2 Drill the holes of the Frame foot H300 to H313, H316 to H331 and H334 to

H341 to the diameter given on Fig. A-FKAAB Sheet 03 and Fig. A-FKAAB

Sheet 04.

3 Drill the holes of the stiffener H314 and H315 to the diameter given on Fig. AFKAAB Sheet 04.

4 Drill the holes of the splice H342 to H354 to the diameter given on Fig. AFKAAB Sheet 05.

(b) Cut-out the Frame foot Item 110 as shown on Fig. A-FKAAB Sheet 03.

Protect the cut-out with:

Wash Primer -

Structure

04CMA2 As required

Primer

Polyurethane Paint

- Corrosion

Inhibiting

04EAC2 As required

(c) Install the fasteners.

Refer to Fig. A-FKAAB

In accordance with SRM 51-40-00, SRM 51-40-20 and SRM 51-40-30

Refer to AMM 20-21-12, Page Block 001

1 Install the fasteners of the Frame foot H300 to H313, H316 to H331 and H334

to H341 to H313 and H316 to H341:

Refer to Fig. A-FKAAB Sheet 03 and Fig. A-FKAAB Sheet 04

2 Screw EN6115V3A7 Item 8

5 Screw EN6115V3A6 Item 10

6 Screw EN6114V5Y8 Item 15

9 Screw EN6115V3A9 Item 33

5 Screw EN6115V3A10 Item 43

6 Screw EN6115V3A11 Item 44

2 Screw ASNA2001V5-12Y Item 50

30 Nut ASNA2529-3 Item 9

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 391

5

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

SERVICE BULLETIN

2 Nut NAS1726-5E Item 14

6 Nut ASNA2529-5 Item 16

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

2 Install the four upper fasteners of the Frame foot:

Refer to Fig. A-FKAAB Sheet 02

4 Bolt Item (55) Retained at

removal

4 Nut NSA5057-6 Item 56

or

4 Nut NSA5057-7 Item 76

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

3 Install the fasteners of the stiffener at STGR 37 H314 and H315:

Refer to Fig. A-FKAAB Sheet 04

2 Rivet ASNA2050DXJ4020 Item 19

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 392

5

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

SERVICE BULLETIN

4 Install the fasteners of the splice H342 to H354:

Refer to Fig. A-FKAAB Sheet 05

1 Screw EN6115V3A7 Item 8

3 Screw EN6115V3A6 Item 10

7 Screw EN6115V3A5 Item 17

2 Screw EN6115V3A4 Item 18

13 Nut ASNA2529-3 Item 9

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

5 Do a sealant bead around the parts with:

Polysulfide Sealant

- Fuel Tank Fillet

06ABB1 As required

(d) Install the Gussets at Frame 46, LH side.

Refer to Fig. A-FUAAB

In accordance with SRM 51-40-20, SRM 51-40-00, SRM 51-40-30 and SRM

51-40-40

Refer to AMM 20-21-12, Page Block 001

1 Put the gussets in position as shown on Fig. A-FUAAB.

1 Gusset Item (141) Retained at

removal

1 Gusset Item (143) Retained at

removal

NOTE: Between the Frame foot and the aft gusset, the distance must

be 2 times the thickness of the gusset.

NOTE: Between the Frame foot and the FWD gusset, the distance

must be 1.3 times the thickness of the gusset.

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 393

5

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

SERVICE BULLETIN

2 Drill holes H332 and H333 to the diameter given on Fig. A-FUAAB Sheet 03.

3 Drill holes H355 and H356 to the diameter given on Fig. A-FUAAB Sheet 03.

4 Install:

1 Gusset Item (141) Retained at

removal

1 Gusset Item (143) Retained at

removal

1 Screw EN6114V6Y14 Item 11

2 Screw EN6114V6Y17 Item 49

1 Screw EN6114V5Y12 Item 51

3 Nut ASNA2529-6 Item 12

1 Nut ASNA2529-5 Item 16

(60) Subtask 536177-831-060-001 - Depending on Inspection results, install the

Fasteners at FR46, RH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 46

Manpower Resources

Manhours 6.00

Minimum number of person 2

Subtask elapsed time 3.00

Skills AIRFRAME

Material necessary to do the job

Component COMPA05

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

9 ASNA2529-3 24 NUT

47 EN6114V3X6 16 SCREW

90 ASNA2019-56-25 24 RIVET

91 EN6114V3X5 8 SCREW

92 EN6080D6X-32 16 RIVET

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

NOTE: The components listed above are only necessary if crack is found on a

Frame foot. The quantity of these items are to be ordered as required.

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 394

5

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

SERVICE BULLETIN

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant - Fuel

Tank Brushable

06ABA1 As required

References

Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001

Structural Repair Manual (SRM) 51-24-00

51-40-00

51-40-20

51-40-30

Fig. A-FVAAA

Removal/Installation of the Fasteners

from FR41 to FR46, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

(a) If removed, install the fasteners at Frame 46, RH side.

Refer to Fig. A-FVAAA

In accordance with SRM 51-40-20, SRM 51-24-00, SRM 51-40-00 and SRM

51-40-30

Refer to AMM 20-21-12, Page Block 001

1 Install:

16 Rivet EN6080D6X-32 Item 92

And:

16 Rivet ASNA2019-56-25 Item 90

or

16 Screw EN6114V3X6 Item 47

16 Nut ASNA2529-3 Item 9

And:

8 Rivet ASNA2019-56-25 Item 90

or

8 Screw EN6114V3X5 Item 91

8 Nut ASNA2529-3 Item 9

NOTE: Protect the fasteners with:

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 395

5

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

SERVICE BULLETIN

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

**CONF 003

(1) Subtask 536177-831-001-001 - Depending on Inspection results, if necessary,

remove the Fasteners from FR41, LH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 41

Manpower Resources

Manhours 4.00

Minimum number of person 2

Subtask elapsed time 2.00

Skills AIRFRAME

References

Structural Repair Manual (SRM) 51-40-20

Fig. A-FVAAA

Removal/Installation of the Fasteners

from FR41 to FR46, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

(a) If necessary, to ease the replacement of the Frame foot, remove fasteners from

Frame 41, LH side.

Refer to Fig. A-FVAAA

In accordance with SRM 51-40-20

1 Remove:

20 Rivet Item (19) Discard

And:

32 Rivet Item (5) Discard

or

32 Bolt Item (3) Discard

32 Nut Item (4) Discard

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 396

5

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

SERVICE BULLETIN

(2) Subtask 536177-831-002-001 - Depending on Inspection results, remove the

Gussets from FR41, LH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 41

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills AIRFRAME

References

Structural Repair Manual (SRM) 51-40-20

Fig. A-FLAAA

Removal/Installation of the Gussets at

FR41, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

(a) Remove the Gussets from Frame 41, LH side.

Refer to Fig. A-FLAAA

In accordance with SRM 51-40-20

1 Remove:

1 Gusset Item (120) Retain

1 Gusset Item (122) Retain

attached with:

4 Screw Item (3) Discard

4 Nut Item (4) Discard

(3) Subtask 536177-831-003-001 - Depending on Inspection results, remove the Frame

Foot from FR41, LH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 41

Manpower Resources

Manhours 16.00

Minimum number of person 2

Subtask elapsed time 8.00

Skills AIRFRAME

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 397

5

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

SERVICE BULLETIN

References

Structural Repair Manual (SRM) 51-40-20

Fig. A-FCAAA

Replacement of the Frame foot FR41,

LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

(a) Remove the Frame foot from Frame 41, LH side.

Refer to Fig. A-FCAAA

In accordance with SRM 51-40-20

1 Remove:

1 Frame foot Item (100) Discard

1 Stiffener Item (58) Retain

1 Splice Item (60) Retain

1 Shim Item (61) Retain

4 Screw Item (55) Retain

4 Nut Item (56) Discard

14 Pin Item (1) Discard

14 Collar Item (2) Discard

30 Screw Item (3) Discard

30 Nut Item (4) Discard

2 Rivet Item (5) Discard

(4) Subtask 536177-831-004-001 - Depending on Inspection results, install an identical

Frame Foot at FR41, LH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 41

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 398

5

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

SERVICE BULLETIN

Manpower Resources

Manhours 16.00

Minimum number of person 2

Subtask elapsed time 8.00

Skills AIRFRAME

Material necessary to do the job

Kit 536177A01R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

8 EN6115V3A7 15 SCREW

9 ASNA2529-3 36 NUT

10 EN6115V3A6 9 SCREW

12 ASNA2529-6 2 NUT

13 ASNA2001V5-8Y 2 SCREW

14 NAS1726-5E 2 NUT

15 EN6114V5Y8 4 SCREW

16 ASNA2529-5 4 NUT

17 EN6115V3A5 10 SCREW

18 EN6115V3A4 2 SCREW

19 ASNA2050DXJ4020 2 RIVET

21 ASNA2529-4 2 NUT

26 EN6114V6X14 2 SCREW

30 EN6114V4X8 1 SCREW

31 EN6114V4X10 1 SCREW

56 NSA5057-6 4 NUT

100 A5711112920095 1 FOOT

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Wash Primer - Structure 04CMA2 As required

Primer Polyurethane Paint -

Corrosion Inhibiting

04EAC2 As required

Polysulfide Sealant -

General Purpose Brushable

06AAA1 As required

Polysulfide Sealant - Fuel

Tank Brushable

06ABA1 As required

Polysulfide Sealant - Fuel

Tank Fillet

06ABB1 As required

References

Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001

Structural Repair Manual (SRM) 51-40-00

51-40-20

51-40-30

51-40-40

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 399

5

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

SERVICE BULLETIN

References

Fig. A-FCAAA

Replacement of the Frame foot FR41,

LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Fig. A-FLAAA

Removal/Installation of the Gussets at

FR41, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

(a) Install and drill all the parts.

Refer to Fig. A-FCAAA

In accordance with SRM 51-40-40

1 Put all the parts in position as shown on Fig. A-FCAAA.

1 Frame foot A5711112920095 Item 100

1 Stiffener Item (58) Retained at

removal

1 Splice Item (60) Retained at

removal

1 Shim Item (61) Retained at

removal

NOTE: If necessary, rework the upper and side surfaces of the Frame

foot with a maximum of 0.5 mm (0.020 in.) as shown on Fig.

A-FCAAA Sheet 03.

NOTE: Between parts apply:

Polysulfide Sealant

- Fuel Tank Fillet

06ABB1 As required

2 Drill the holes of the Frame foot H1 to H23 and H26 to H31 to the diameter

given on Fig. A-FCAAA Sheet 03 and Fig. A-FCAAA Sheet 04.

3 Drill the holes of the stiffener H45 and H46 to the diameter given on Fig. AFCAAA Sheet 04.

4 Drill the holes of the splice H32 to H44 to the diameter given on Fig. A-FCAAA

Sheet 05.

(b) Cut-out the Frame foot Item 100 as shown on Fig. A-FCAAA Sheet 03.

Protect the cut-out with:

Wash Primer -

Structure

04CMA2 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 400

5

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

SERVICE BULLETIN

Primer

Polyurethane Paint

- Corrosion

Inhibiting

04EAC2 As required

(c) Install the fasteners.

Refer to Fig. A-FCAAA

In accordance with SRM 51-40-00, SRM 51-40-20 and SRM 51-40-30

Refer to AMM 20-21-12, Page Block 001

1 Install the fasteners of the Frame foot H1 to H23 and H26 to H31:

Refer to Fig. A-FCAAA Sheet 03 and Fig. A-FCAAA Sheet 04

14 Screw EN6115V3A7 Item 8

9 Screw EN6115V3A6 Item 10

2 Screw ASNA2001V5-8Y Item 13

4 Screw EN6114V5Y8 Item 15

23 Nut ASNA2529-3 Item 9

2 Nut NAS1726-5E Item 14

4 Nut ASNA2529-5 Item 16

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

2 Install the four upper fasteners of the Frame foot:

Refer to Fig. A-FCAAA Sheet 02

4 Screw Item (55) Retained at

removal

4 Nut NSA5057-6 Item 56

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 401

5

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

SERVICE BULLETIN

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

3 Install the fasteners of the stiffener at STGR 36 H45 and H46:

Refer to Fig. A-FCAAA Sheet 04

2 Rivet ASNA2050DXJ4020 Item 19

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

4 Install the fasteners of the splice H32 to H44:

Refer to Fig. A-FCAAA Sheet 05

1 Screw EN6115V3A7 Item 8

10 Screw EN6115V3A5 Item 17

2 Screw EN6115V3A4 Item 18

13 Nut ASNA2529-3 Item 9

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

5 Do a sealant bead around the parts with:

Polysulfide Sealant

- Fuel Tank Fillet

06ABB1 As required

(d) Install the Gussets at Frame 41, LH side.

Refer to Fig. A-FLAAA

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 402

5

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

SERVICE BULLETIN

In accordance with SRM 51-40-20, SRM 51-40-00 and SRM 51-40-30

Refer to AMM 20-21-12, Page Block 001

1 Put the gussets in position as shown on Fig. A-FLAAA Sheet 02 and Fig. AFLAAA Sheet 03.

1 Gusset Item (120) Retained at

removal

1 Gusset Item (122) Retained at

removal

NOTE: Between the Frame foot and the aft gusset, the distance must

be 2 times the thickness of the gusset.

NOTE: Between the Frame foot and the FWD gusset, the distance

must be 1.3 times the thickness of the gusset.

2 Drill holes H24 and H25 to the diameter given on Fig. A-FLAAA Sheet 03.

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

4 Install:

1 Gusset Item (120) Retained at

removal

1 Gusset Item (122) Retained at

removal

2 Screw EN6114V6X14 Item 26

1 Screw EN6114V4X8 Item 30

1 Screw EN6114V4X10 Item 31

2 Nut ASNA2529-6 Item 12

2 Nut ASNA2529-4 Item 21

(5) Subtask 536177-831-005-001 - Depending on Inspection results, if removed, install

the Fasteners at FR41, LH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 41

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 403

5

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

SERVICE BULLETIN

Manpower Resources

Manhours 6.00

Minimum number of person 2

Subtask elapsed time 3.00

Skills AIRFRAME

Material necessary to do the job

Component COMPA01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

9 ASNA2529-3 32 NUT

90 ASNA2019-56-25 32 RIVET

91 EN6114V3X5 32 SCREW

92 EN6080D6X-32 20 RIVET

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

NOTE: The components listed above are only necessary if crack is found on a

Frame foot. The quantity of these items are to be ordered as required.

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant - Fuel

Tank Brushable

06ABA1 As required

References

Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001

Structural Repair Manual (SRM) 51-24-00

51-40-00

51-40-20

51-40-30

Fig. A-FVAAA

Removal/Installation of the Fasteners

from FR41 to FR46, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

(a) If removed, install the fasteners at Frame 41, LH side.

Refer to Fig. A-FVAAA

In accordance with SRM 51-40-20, SRM 51-24-00, SRM 51-40-00 and SRM

51-40-30

Refer to AMM 20-21-12, Page Block 001

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 404

5

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

SERVICE BULLETIN

1 Install:

20 Rivet EN6080D6X-32 Item 92

And:

32 Rivet ASNA2019-56-25 Item 90

or

32 Screw EN6114V3X5 Item 91

32 Nut ASNA2529-3 Item 9

NOTE: Protect the fasteners with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

(6) Subtask 536177-831-006-001 - Depending on Inspection results, if necessary,

remove the Fasteners from FR41, RH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 41

Manpower Resources

Manhours 4.00

Minimum number of person 2

Subtask elapsed time 2.00

Skills AIRFRAME

References

Structural Repair Manual (SRM) 51-40-20

Fig. A-FVAAA

Removal/Installation of the Fasteners

from FR41 to FR46, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

(a) If necessary, to ease the replacement of the Frame foot, remove fasteners from

Frame 41, RH side.

Refer to Fig. A-FVAAA

In accordance with SRM 51-40-20

1 Remove:

20 Rivet Item (19) Discard

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 405

5

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

SERVICE BULLETIN

And:

32 Rivet Item (5) Discard

or

32 Bolt Item (3) Discard

32 Nut Item (4) Discard

(7) Subtask 536177-831-007-001 - Depending on Inspection results, remove the

Gussets from FR41, RH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 41

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills AIRFRAME

References

Structural Repair Manual (SRM) 51-40-20

Fig. A-FLAAA

Removal/Installation of the Gussets at

FR41, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

(a) Remove the Gussets from Frame 41, RH side.

Refer to Fig. A-FLAAA

In accordance with SRM 51-40-20

1 Remove:

1 Gusset Item (121) Retain

1 Gusset Item (123) Retain

attached with:

4 Screw Item (3) Discard

4 Nut Item (4) Discard

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 406

5

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

SERVICE BULLETIN

(8) Subtask 536177-831-008-001 - Depending on Inspection results, remove the Frame

Foot from FR41, RH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 41

Manpower Resources

Manhours 16.00

Minimum number of person 2

Subtask elapsed time 8.00

Skills AIRFRAME

References

Structural Repair Manual (SRM) 51-40-20

Fig. A-FCAAA

Replacement of the Frame foot FR41,

LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

(a) Remove the Frame foot from Frame 41, RH side.

Refer to Fig. A-FCAAA

In accordance with SRM 51-40-20

1 Remove:

1 Frame foot Item (101) Discard

1 Stiffener Item (57) Retain

1 Splice Item (59) Retain

1 Shim Item (61) Retain

4 Screw Item (55) Retain

4 Nut Item (56) Discard

14 Pin Item (1) Discard

14 Collar Item (2) Discard

30 Screw Item (3) Discard

30 Nut Item (4) Discard

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 407

5

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

SERVICE BULLETIN

2 Rivet Item (5) Discard

(9) Subtask 536177-831-009-001 - Depending on Inspection results, install an identical

Frame Foot at FR41, RH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 41

Manpower Resources

Manhours 16.00

Minimum number of person 2

Subtask elapsed time 8.00

Skills AIRFRAME

Material necessary to do the job

Kit 536177A19R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

8 EN6115V3A7 15 SCREW

9 ASNA2529-3 36 NUT

10 EN6115V3A6 9 SCREW

12 ASNA2529-6 2 NUT

13 ASNA2001V5-8Y 2 SCREW

14 NAS1726-5E 2 NUT

15 EN6114V5Y8 4 SCREW

16 ASNA2529-5 4 NUT

17 EN6115V3A5 10 SCREW

18 EN6115V3A4 2 SCREW

19 ASNA2050DXJ4020 2 RIVET

21 ASNA2529-4 2 NUT

26 EN6114V6X14 2 SCREW

30 EN6114V4X8 1 SCREW

31 EN6114V4X10 1 SCREW

56 NSA5057-6 4 NUT

101 A5711112920195 1 FOOT

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Wash Primer - Structure 04CMA2 As required

Primer Polyurethane Paint -

Corrosion Inhibiting

04EAC2 As required

Polysulfide Sealant -

General Purpose Brushable

06AAA1 As required

Polysulfide Sealant - Fuel

Tank Brushable

06ABA1 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 408

5

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

SERVICE BULLETIN

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant - Fuel

Tank Fillet

06ABB1 As required

References

Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001

Structural Repair Manual (SRM) 51-40-00

51-40-20

51-40-30

51-40-40

Fig. A-FCAAA

Replacement of the Frame foot FR41,

LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Fig. A-FLAAA

Removal/Installation of the Gussets at

FR41, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

(a) Install and drill all the parts.

Refer to Fig. A-FCAAA

In accordance with SRM 51-40-40

1 Put all the parts in position as shown on Fig. A-FCAAA.

1 Frame foot A5711112920195 Item 101

1 Stiffener Item (57) Retained at

removal

1 Splice Item (59) Retained at

removal

1 Shim Item (61) Retained at

removal

NOTE: If necessary, rework the upper and side surfaces of the Frame

foot with a maximum of 0.5 mm (0.020 in.) as shown on Fig.

A-FCAAA Sheet 03.

NOTE: Between parts apply:

Polysulfide Sealant

- Fuel Tank Fillet

06ABB1 As required

2 Drill the holes of the Frame foot H1 to H23 and H26 to H31 to the diameter

given on Fig. A-FCAAA Sheet 03 and Fig. A-FCAAA Sheet 04.

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 409

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@A300-600

SERVICE BULLETIN

3 Drill the holes of the stiffener H45 and H46 to the diameter given on Fig. AFCAAA Sheet 04.

4 Drill the holes of the splice H32 to H44 to the diameter given on Fig. A-FCAAA

Sheet 05.

(b) Cut-out the Frame foot Item 100 as shown on Fig. A-FCAAA Sheet 03.

Protect the cut-out with:

Wash Primer -

Structure

04CMA2 As required

Primer

Polyurethane Paint

- Corrosion

Inhibiting

04EAC2 As required

(c) Install the fasteners.

Refer to Fig. A-FCAAA

In accordance with SRM 51-40-00, SRM 51-40-20 and SRM 51-40-30

Refer to AMM 20-21-12, Page Block 001

1 Install the fasteners of the Frame foot H1 to H23 and H26 to H31:

Refer to Fig. A-FCAAA Sheet 03 and Fig. A-FCAAA Sheet 04

14 Screw EN6115V3A7 Item 8

9 Screw EN6115V3A6 Item 10

2 Screw ASNA2001V5-8Y Item 13

4 Screw EN6114V5Y8 Item 15

23 Nut ASNA2529-3 Item 9

2 Nut NAS1726-5E Item 14

4 Nut ASNA2529-5 Item 16

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

2 Install the four upper fasteners of the Frame foot:

Refer to Fig. A-FCAAA Sheet 02

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 410

5

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

SERVICE BULLETIN

4 Screw Item (55) Retained at

removal

4 Nut NSA5057-6 Item 56

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

3 Install the fasteners of the stiffener at STGR 36 H45 and H46:

Refer to Fig. A-FCAAA Sheet 04

2 Rivet ASNA2050DXJ4020 Item 19

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

4 Install the fasteners of the splice H32 to H44:

Refer to Fig. A-FCAAA Sheet 05

1 Screw EN6115V3A7 Item 8

10 Screw EN6115V3A5 Item 17

2 Screw EN6115V3A4 Item 18

13 Nut ASNA2529-3 Item 9

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 411

5

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

SERVICE BULLETIN

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

5 Do a sealant bead around the parts with:

Polysulfide Sealant

- Fuel Tank Fillet

06ABB1 As required

(d) Install the Gussets at Frame 41, LH side.

Refer to Fig. A-FLAAA

In accordance with SRM 51-40-20, SRM 51-40-00 and SRM 51-40-30

Refer to AMM 20-21-12, Page Block 001

1 Put the gussets in position as shown on Fig. A-FLAAA Sheet 02 and Fig. AFLAAA Sheet 03.

1 Gusset Item (121) Retained at

removal

1 Gusset Item (123) Retained at

removal

NOTE: Between the Frame foot and the aft gusset, the distance must

be 2 times the thickness of the gusset.

NOTE: Between the Frame foot and the FWD gusset, the distance

must be 1.3 times the thickness of the gusset.

2 Drill holes H24 and H25 to the diameter given on Fig. A-FLAAA Sheet 03.

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

4 Install:

1 Gusset Item (121) Retained at

removal

1 Gusset Item (123) Retained at

removal

2 Screw EN6114V6X14 Item 26

1 Screw EN6114V4X8 Item 30

1 Screw EN6114V4X10 Item 31

2 Nut ASNA2529-6 Item 12

2 Nut ASNA2529-4 Item 21

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 412

5

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

SERVICE BULLETIN

(10) Subtask 536177-831-010-001 - Depending on Inspection results, if removed, install

the Fasteners at FR41, RH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 41

Manpower Resources

Manhours 6.00

Minimum number of person 2

Subtask elapsed time 3.00

Skills AIRFRAME

Material necessary to do the job

Component COMPA01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

9 ASNA2529-3 32 NUT

90 ASNA2019-56-25 32 RIVET

91 EN6114V3X5 32 SCREW

92 EN6080D6X-32 20 RIVET

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

NOTE: The components listed above are only necessary if crack is found on a

Frame foot. The quantity of these items are to be ordered as required.

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant - Fuel

Tank Brushable

06ABA1 As required

References

Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001

Structural Repair Manual (SRM) 51-24-00

51-40-00

51-40-20

51-40-30

Fig. A-FVAAA

Removal/Installation of the Fasteners

from FR41 to FR46, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 413

5

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

SERVICE BULLETIN

(a) If removed, install the fasteners at Frame 41, RH side.

Refer to Fig. A-FVAAA

In accordance with SRM 51-40-20, SRM 51-24-00, SRM 51-40-00 and SRM

51-40-30

Refer to AMM 20-21-12, Page Block 001

1 Install:

20 Rivet EN6080D6X-32 Item 92

And:

32 Rivet ASNA2019-56-25 Item 90

or

32 Screw EN6114V3X5 Item 91

32 Nut ASNA2529-3 Item 9

NOTE: Protect the fasteners with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

(11) Subtask 536177-831-011-001 - Depending on Inspection results, if necessary,

remove the Fasteners from FR42, LH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 42

Manpower Resources

Manhours 4.00

Minimum number of person 2

Subtask elapsed time 2.00

Skills AIRFRAME

References

Structural Repair Manual (SRM) 51-40-20

Fig. A-FVAAA

Removal/Installation of the Fasteners

from FR41 to FR46, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 414

5

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

SERVICE BULLETIN

(a) If necessary, to ease the replacement of the Frame foot, remove fasteners from

Frame 42, LH side.

Refer to Fig. A-FVAAA

In accordance with SRM 51-40-20

1 Remove:

16 Rivet Item (19) Discard

And:

24 Rivet Item (5) Discard

or

24 Bolt Item (3) Discard

24 Nut Item (4) Discard

(12) Subtask 536177-831-012-001 - Depending on Inspection results, remove the

Gussets from FR42, LH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 42

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills AIRFRAME

References

Structural Repair Manual (SRM) 51-40-20

Fig. A-FNAAA

Removal/Installation of the Gussets at

FR42, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

(a) Remove the Gussets from Frame 42, LH side.

Refer to Fig. A-FNAAA

In accordance with SRM 51-40-20

1 Remove:

1 Gusset Item (124) Retain

1 Gusset Item (126) Retain

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 415

5

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

SERVICE BULLETIN

attached with:

4 Screw Item (3) Discard

4 Nut Item (4) Discard

(13) Subtask 536177-831-013-001 - Depending on Inspection results, remove the Frame

Foot from FR42, LH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 42

Manpower Resources

Manhours 16.00

Minimum number of person 2

Subtask elapsed time 8.00

Skills AIRFRAME

References

Structural Repair Manual (SRM) 51-40-20

Fig. A-FDAAA

Replacement of the Frame foot FR42,

LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

(a) Remove the Frame foot from Frame 42, LH side.

Refer to Fig. A-FDAAA

In accordance with SRM 51-40-20

1 Remove:

1 Frame foot Item (102) Discard

1 Doubler Item (62) Retain

1 Shim Item (63) Retain

1 Shim Item (64) Retain

1 Shim Item (65) Retain

1 Stiffener Item (58) Retain

1 Stiffener Item (68) Retain

1 Splice Item (66) Retain

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 416

5

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

SERVICE BULLETIN

4 Screw Item (55) Retain

4 Nut Item (56) Discard

28 Pin Item (1) Discard

28 Collar Item (2) Discard

31 Screw Item (3) Discard

31 Nut Item (4) Discard

6 Rivet Item (5) Discard

(14) Subtask 536177-831-014-001 - Depending on Inspection results, install an identical

Frame Foot at FR42, LH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 42

Manpower Resources

Manhours 16.00

Minimum number of person 2

Subtask elapsed time 8.00

Skills AIRFRAME

Material necessary to do the job

Kit 536177A04R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

8 EN6115V3A7 1 SCREW

9 ASNA2529-3 53 NUT

10 EN6115V3A6 11 SCREW

12 ASNA2529-6 2 NUT

13 ASNA2001V5-8Y 2 SCREW

14 NAS1726-5E 2 NUT

15 EN6114V5Y8 8 SCREW

16 ASNA2529-5 8 NUT

17 EN6115V3A5 10 SCREW

18 EN6115V3A4 4 SCREW

19 ASNA2050DXJ4020 4 RIVET

21 ASNA2529-4 2 NUT

30 EN6114V4X8 1 SCREW

31 EN6114V4X10 1 SCREW

32 EN6115V3A8 14 SCREW

33 EN6115V3A9 11 SCREW

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 417

5

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

SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

35 EN6114V6X13 2 SCREW

56 NSA5057-6 4 NUT

102 A5711113020095 1 FOOT

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Wash Primer - Structure 04CMA2 As required

Primer Polyurethane Paint -

Corrosion Inhibiting

04EAC2 As required

Polysulfide Sealant -

General Purpose Brushable

06AAA1 As required

Polysulfide Sealant - Fuel

Tank Brushable

06ABA1 As required

Polysulfide Sealant - Fuel

Tank Fillet

06ABB1 As required

References

Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001

Structural Repair Manual (SRM) 51-40-00

51-40-20

51-40-30

51-40-40

Fig. A-FDAAA

Replacement of the Frame foot FR42,

LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Fig. A-FNAAA

Removal/Installation of the Gussets at

FR42, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

(a) Install and drill all the parts.

Refer to Fig. A-FDAAA

In accordance with SRM 51-40-40

1 Put all the parts in position as shown on Fig. A-FDAAA

1 Frame foot A5711113020095 Item 102

1 Doubler Item (62) Retained at

removal

1 Shim Item (63) Retained at

removal

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 418

5

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

SERVICE BULLETIN

1 Shim Item (64) Retained at

removal

1 Shim Item (65) Retained at

removal

1 Splice Item (66) Retained at

removal

1 Stiffener Item (58) Retained at

removal

1 Stiffener Item (68) Retained at

removal

NOTE: If necessary, rework the upper and side surfaces of the Frame

foot with a maximum of 0.5 mm (0.020 in.) as shown on Fig.

A-FDAAA Sheet 03.

NOTE: Between parts apply:

Polysulfide Sealant

- Fuel Tank Fillet

06ABB1 As required

2 Drill the holes of the Frame foot H51 to H78, H83 to H90 and H93 to H102 to

the diameter given on Fig. A-FDAAA Sheet 03 to Fig. A-FDAAA Sheet 05.

3 Drill the holes of the stiffener at STGR 37 H81, H82, H103 and H104 to the

diameter given on Fig. A-FDAAA Sheet 05.

4 Drill the holes of the splice H105 to H117 to the diameter given on Fig. AFDAAA Sheet 05.

(b) Cut-out the Frame foot Item 102 as shown on Fig. A-FDAAA Sheet 03.

Protect the cut-out with:

Wash Primer -

Structure

04CMA2 As required

Primer

Polyurethane Paint

- Corrosion

Inhibiting

04EAC2 As required

(c) Install the fasteners.

Refer to Fig. A-FDAAA

In accordance with SRM 51-40-00, SRM 51-40-20 and SRM 51-40-30

Refer to AMM 20-21-12, Page Block 001

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 419

5

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

SERVICE BULLETIN

11 Screw EN6115V3A6 Item 10

2 Screw ASNA2001V5-8Y Item 13

8 Screw EN6114V5Y8 Item 15

14 Screw EN6115V3A8 Item 32

11 Screw EN6115V3A9 Item 33

36 Nut ASNA2529-3 Item 9

2 Nut NAS1726-5E Item 14

8 Nut ASNA2529-5 Item 16

1 Install the fasteners of the Frame foot H51 to H78, H83 to H90 and H93 to

H102:

Refer to Fig. A-FDAAA Sheet 03 and Fig. A-FDAAA Sheet 04

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

2 Install the four upper fasteners of the Frame foot:

Refer to Fig. A-FDAAA Sheet 02

4 Screw Item (55) Retained at

removal

4 Nut NSA5057-6 Item 56

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

3 Install the fasteners of the stiffener at STGR 36 H79 and H80:

Refer to Fig. A-FDAAA Sheet 04

2 Rivet ASNA2050DXJ4020 Item 19

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 420

5

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

SERVICE BULLETIN

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

4 Install the fasteners of the stiffener at STGR 37 H81, H82, H103 and H104:

Refer to Fig. A-FDAAA Sheet 05

2 Screw EN6115V3A4 Item 18

2 Nut ASNA2529-3 Item 9

2 Rivet ASNA2050DXJ4020 Item 19

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

5 Install the fasteners of the splice H105 to H117:

Refer to Fig. A-FDAAA Sheet 05

1 Screw EN6115V3A7 Item 8

10 Screw EN6115V3A5 Item 17

2 Screw EN6115V3A4 Item 18

15 Nut ASNA2529-3 Item 9

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 421

5

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

SERVICE BULLETIN

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

6 Do a sealant bead around the parts with:

Polysulfide Sealant

- Fuel Tank Fillet

06ABB1 As required

(d) Install the Gussets at Frame 42, LH side.

Refer to Fig. A-FNAAA

In accordance with SRM 51-40-20, SRM 51-40-00, SRM 51-40-30 and SRM

51-40-40

Refer to AMM 20-21-12, Page Block 001

1 Put the gussets in position as shown on Fig. A-FNAAA.

1 Gusset Item (124) Retained at

removal

1 Gusset Item (126) Retained at

removal

NOTE: Between the Frame foot and the aft gusset, the distance must

be 2 times the thickness of the gusset.

NOTE: Between the Frame foot and the FWD gusset, the distance

must be 1.3 times the thickness of the gusset.

2 Drill holes H91 and H92 to the diameter given on Fig. A-FNAAA Sheet 03.

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

4 Install:

1 Gusset Item (124) Retained at

removal

1 Gusset Item (126) Retained at

removal

1 Screw EN6114V4X8 Item 30

1 Screw EN6114V4X10 Item 31

2 Screw EN6114V6X13 Item 35

2 Nut ASNA2529-6 Item 12

2 Nut ASNA2529-4 Item 21

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 422

5

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

SERVICE BULLETIN

(15) Subtask 536177-831-015-001 - Depending on Inspection results, if removed, install

the Fasteners at FR42, LH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 42

Manpower Resources

Manhours 6.00

Minimum number of person 2

Subtask elapsed time 3.00

Skills AIRFRAME

Material necessary to do the job

Component COMPA02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

9 ASNA2529-3 24 NUT

90 ASNA2019-56-25 24 RIVET

91 EN6114V3X5 24 SCREW

92 EN6080D6X-32 16 RIVET

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

NOTE: The components listed above are only necessary if crack is found on a

Frame foot. The quantity of these items are to be ordered as required.

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant - Fuel

Tank Brushable

06ABA1 As required

References

Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001

Structural Repair Manual (SRM) 51-24-00

51-40-00

51-40-20

51-40-30

Fig. A-FVAAA

Removal/Installation of the Fasteners

from FR41 to FR46, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 423

5

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

SERVICE BULLETIN

(a) If removed, install the fasteners at Frame 42, LH side.

Refer to Fig. A-FVAAA

In accordance with SRM 51-40-20, SRM 51-24-00, SRM 51-40-00 and SRM

51-40-30

Refer to AMM 20-21-12, Page Block 001

1 Install:

16 Rivet EN6080D6X-32 Item 92

And:

24 Rivet ASNA2019-56-25 Item 90

or

24 Screw EN6114V3X5 Item 91

24 Nut ASNA2529-3 Item 9

NOTE: Protect the fasteners with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

(16) Subtask 536177-831-016-001 - Depending on Inspection results, if necessary,

remove the Fasteners from FR42, RH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 42

Manpower Resources

Manhours 4.00

Minimum number of person 2

Subtask elapsed time 2.00

Skills AIRFRAME

References

Structural Repair Manual (SRM) 51-40-20

Fig. A-FVAAA

Removal/Installation of the Fasteners

from FR41 to FR46, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 424

5

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

SERVICE BULLETIN

(a) If necessary, to ease the replacement of the Frame foot, remove fasteners from

Frame 42, RH side.

Refer to Fig. A-FVAAA

In accordance with SRM 51-40-20

1 Remove:

16 Rivet Item (19) Discard

And:

24 Rivet Item (5) Discard

or

24 Bolt Item (3) Discard

24 Nut Item (4) Discard

(17) Subtask 536177-831-017-001 - Depending on Inspection results, remove the

Gussets from FR42, RH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 42

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills AIRFRAME

References

Structural Repair Manual (SRM) 51-40-20

Fig. A-FNAAA

Removal/Installation of the Gussets at

FR42, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

(a) Remove the Gussets from Frame 42, RH side.

Refer to Fig. A-FNAAA

In accordance with SRM 51-40-20

1 Remove:

1 Gusset Item (125) Retain

1 Gusset Item (127) Retain

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 425

5

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

SERVICE BULLETIN

attached with:

4 Screw Item (3) Discard

4 Nut Item (4) Discard

(18) Subtask 536177-831-018-001 - Depending on Inspection results, remove the Frame

Foot from FR42, RH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 42

Manpower Resources

Manhours 16.00

Minimum number of person 2

Subtask elapsed time 8.00

Skills AIRFRAME

References

Structural Repair Manual (SRM) 51-40-20

Fig. A-FDAAA

Replacement of the Frame foot FR42,

LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

(a) Remove the Frame foot from Frame 42, RH side.

Refer to Fig. A-FDAAA

In accordance with SRM 51-40-20

1 Remove:

1 Frame foot Item (103) Discard

1 Doubler Item (62) Retain

1 Shim Item (63) Retain

1 Shim Item (64) Retain

1 Shim Item (65) Retain

1 Stiffener Item (57) Retain

1 Stiffener Item (69) Retain

1 Splice Item (67) Retain

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 426

5

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

SERVICE BULLETIN

4 Screw Item (55) Retain

4 Nut Item (56) Discard

28 Pin Item (1) Discard

28 Collar Item (2) Discard

31 Screw Item (3) Discard

31 Nut Item (4) Discard

6 Rivet Item (5) Discard

(19) Subtask 536177-831-019-001 - Depending on Inspection results, install an identical

Frame Foot at FR42, RH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 42

Manpower Resources

Manhours 16.00

Minimum number of person 2

Subtask elapsed time 8.00

Skills AIRFRAME

Material necessary to do the job

Kit 536177A22R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

8 EN6115V3A7 1 SCREW

9 ASNA2529-3 53 NUT

10 EN6115V3A6 11 SCREW

12 ASNA2529-6 2 NUT

13 ASNA2001V5-8Y 2 SCREW

14 NAS1726-5E 2 NUT

15 EN6114V5Y8 8 SCREW

16 ASNA2529-5 8 NUT

17 EN6115V3A5 10 SCREW

18 EN6115V3A4 4 SCREW

19 ASNA2050DXJ4020 4 RIVET

21 ASNA2529-4 2 NUT

30 EN6114V4X8 1 SCREW

31 EN6114V4X10 1 SCREW

32 EN6115V3A8 14 SCREW

33 EN6115V3A9 11 SCREW

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 427

5

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

SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

35 EN6114V6X13 2 SCREW

56 NSA5057-6 4 NUT

103 A5711113020195 1 FOOT

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Wash Primer - Structure 04CMA2 As required

Primer Polyurethane Paint -

Corrosion Inhibiting

04EAC2 As required

Polysulfide Sealant -

General Purpose Brushable

06AAA1 As required

Polysulfide Sealant - Fuel

Tank Brushable

06ABA1 As required

Polysulfide Sealant - Fuel

Tank Fillet

06ABB1 As required

References

Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001

Structural Repair Manual (SRM) 51-40-00

51-40-20

51-40-30

51-40-40

Fig. A-FDAAA

Replacement of the Frame foot FR42,

LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Fig. A-FNAAA

Removal/Installation of the Gussets at

FR42, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

(a) Install and drill all the parts.

Refer to Fig. A-FDAAA

In accordance with SRM 51-40-40

1 Put all the parts in position as shown on Fig. A-FDAAA

1 Frame foot A5711113020195 Item 103

1 Doubler Item (62) Retained at

removal

1 Shim Item (63) Retained at

removal

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 428

5

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

SERVICE BULLETIN

1 Shim Item (64) Retained at

removal

1 Shim Item (65) Retained at

removal

1 Splice Item (67) Retained at

removal

1 Stiffener Item (57) Retained at

removal

1 Stiffener Item (69) Retained at

removal

NOTE: If necessary, rework the upper and side surfaces of the Frame

foot with a maximum of 0.5 mm (0.020 in.) as shown on Fig.

A-FDAAA Sheet 03.

NOTE: Between parts apply:

Polysulfide Sealant

- Fuel Tank Fillet

06ABB1 As required

2 Drill the holes of the Frame foot H51 to H78, H83 to H90 and H93 to H102 to

the diameter given on Fig. A-FDAAA Sheet 03 to Fig. A-FDAAA Sheet 05.

3 Drill the holes of the stiffener at STGR 37 H81, H82, H103 and H104 to the

diameter given on Fig. A-FDAAA Sheet 05.

4 Drill the holes of the splice H105 to H117 to the diameter given on Fig. AFDAAA Sheet 05.

(b) Cut-out the Frame foot Item 102 as shown on Fig. A-FDAAA Sheet 03.

Protect the cut-out with:

Wash Primer -

Structure

04CMA2 As required

Primer

Polyurethane Paint

- Corrosion

Inhibiting

04EAC2 As required

(c) Install the fasteners.

Refer to Fig. A-FDAAA

In accordance with SRM 51-40-00, SRM 51-40-20 and SRM 51-40-30

Refer to AMM 20-21-12, Page Block 001

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 429

5

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

SERVICE BULLETIN

11 Screw EN6115V3A6 Item 10

2 Screw ASNA2001V5-8Y Item 13

8 Screw EN6114V5Y8 Item 15

14 Screw EN6115V3A8 Item 32

11 Screw EN6115V3A9 Item 33

36 Nut ASNA2529-3 Item 9

2 Nut NAS1726-5E Item 14

8 Nut ASNA2529-5 Item 16

1 Install the fasteners of the Frame foot H51 to H78, H83 to H90 and H93 to

H102:

Refer to Fig. A-FDAAA Sheet 03 and Fig. A-FDAAA Sheet 04

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

2 Install the four upper fasteners of the Frame foot:

Refer to Fig. A-FDAAA Sheet 02

4 Screw Item (55) Retained at

removal

4 Nut NSA5057-6 Item 56

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

3 Install the fasteners of the stiffener at STGR 36 H79 and H80:

Refer to Fig. A-FDAAA Sheet 04

2 Rivet ASNA2050DXJ4020 Item 19

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 430

5

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

SERVICE BULLETIN

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

4 Install the fasteners of the stiffener at STGR 37 H81, H82, H103 and H104:

Refer to Fig. A-FDAAA Sheet 05

2 Screw EN6115V3A4 Item 18

2 Nut ASNA2529-3 Item 9

2 Rivet ASNA2050DXJ4020 Item 19

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

5 Install the fasteners of the splice H105 to H117:

Refer to Fig. A-FDAAA Sheet 05

1 Screw EN6115V3A7 Item 8

10 Screw EN6115V3A5 Item 17

2 Screw EN6115V3A4 Item 18

15 Nut ASNA2529-3 Item 9

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 431

5

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

SERVICE BULLETIN

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

6 Do a sealant bead around the parts with:

Polysulfide Sealant

- Fuel Tank Fillet

06ABB1 As required

(d) Install the Gussets at Frame 42, LH side.

Refer to Fig. A-FNAAA

In accordance with SRM 51-40-20, SRM 51-40-00, SRM 51-40-30 and SRM

51-40-40

Refer to AMM 20-21-12, Page Block 001

1 Put the gussets in position as shown on Fig. A-FNAAA.

1 Gusset Item (125) Retained at

removal

1 Gusset Item (127) Retained at

removal

NOTE: Between the Frame foot and the aft gusset, the distance must

be 2 times the thickness of the gusset.

NOTE: Between the Frame foot and the FWD gusset, the distance

must be 1.3 times the thickness of the gusset.

2 Drill holes H91 and H92 to the diameter given on Fig. A-FNAAA Sheet 03.

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

4 Install:

1 Gusset Item (125) Retained at

removal

1 Gusset Item (127) Retained at

removal

1 Screw EN6114V4X8 Item 30

1 Screw EN6114V4X10 Item 31

2 Screw EN6114V6X13 Item 35

2 Nut ASNA2529-6 Item 12

2 Nut ASNA2529-4 Item 21

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 432

5

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

SERVICE BULLETIN

(20) Subtask 536177-831-020-001 - Depending on Inspection results, if removed, install

the Fasteners at FR42, RH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 42

Manpower Resources

Manhours 6.00

Minimum number of person 2

Subtask elapsed time 3.00

Skills AIRFRAME

Material necessary to do the job

Component COMPA02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

9 ASNA2529-3 24 NUT

90 ASNA2019-56-25 24 RIVET

91 EN6114V3X5 24 SCREW

92 EN6080D6X-32 16 RIVET

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

NOTE: The components listed above are only necessary if crack is found on a

Frame foot. The quantity of these items are to be ordered as required.

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant - Fuel

Tank Brushable

06ABA1 As required

References

Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001

Structural Repair Manual (SRM) 51-24-00

51-40-00

51-40-20

51-40-30

Fig. A-FVAAA

Removal/Installation of the Fasteners

from FR41 to FR46, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 433

5

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

SERVICE BULLETIN

(a) If removed, install the fasteners at Frame 42, RH side.

Refer to Fig. A-FVAAA

In accordance with SRM 51-40-20, SRM 51-24-00, SRM 51-40-00 and SRM

51-40-30

Refer to AMM 20-21-12, Page Block 001

1 Install:

16 Rivet EN6080D6X-32 Item 92

And:

24 Rivet ASNA2019-56-25 Item 90

or

24 Screw EN6114V3X5 Item 91

24 Nut ASNA2529-3 Item 9

NOTE: Protect the fasteners with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

(21) Subtask 536177-831-021-001 - Depending on Inspection results, if necessary,

remove the Fasteners from FR43, LH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 43

Manpower Resources

Manhours 4.00

Minimum number of person 2

Subtask elapsed time 2.00

Skills AIRFRAME

References

Structural Repair Manual (SRM) 51-40-20

Fig. A-FVAAA

Removal/Installation of the Fasteners

from FR41 to FR46, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 434

5

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

SERVICE BULLETIN

(a) If necessary, to ease the replacement of the Frame foot, remove fasteners from

Frame 43, LH side.

Refer to Fig. A-FVAAA

In accordance with SRM 51-40-20

1 Remove:

16 Rivet Item (19) Discard

And:

24 Rivet Item (5) Discard

or

24 Bolt Item (3) Discard

24 Nut Item (4) Discard

(22) Subtask 536177-831-022-001 - Depending on Inspection results, remove the

Gussets from FR43, LH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 43

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills AIRFRAME

References

Structural Repair Manual (SRM) 51-40-20

Fig. A-FPAAA

Removal/Installation of the Gussets at

FR43, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

(a) Remove the Gussets from Frame 43, LH side.

Refer to Fig. A-FPAAA

In accordance with SRM 51-40-20

1 Remove:

1 Gusset Item (128) Retain

1 Gusset Item (130) Retain

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 435

5

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

SERVICE BULLETIN

attached with:

4 Screw Item (3) Discard

4 Nut Item (4) Discard

(23) Subtask 536177-831-023-001 - Depending on Inspection results, remove the Frame

Foot from FR43, LH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 43

Manpower Resources

Manhours 16.00

Minimum number of person 2

Subtask elapsed time 8.00

Skills AIRFRAME

References

Structural Repair Manual (SRM) 51-40-20

Fig. A-FEAAA

Replacement of the Frame foot FR43,

LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

(a) Remove the Frame foot from Frame 43, LH side.

Refer to Fig. A-FEAAA

In accordance with SRM 51-40-20

1 Remove:

1 Frame foot Item (104) Discard

1 Stiffener Item (58) Retain

1 Shim Item (70) Retain

1 Splice Item (72) Retain

4 Bolt Item (55) Retain

4 Nut Item (56) Discard

16 Pin Item (1) Discard

16 Collar Item (2) Discard

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 436

5

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

SERVICE BULLETIN

31 Bolt Item (3) Discard

31 Nut Item (4) Discard

2 Rivet Item (5) Discard

(24) Subtask 536177-831-024-001 - Depending on Inspection results, install an identical

Frame Foot at FR43, LH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 43

Manpower Resources

Manhours 16.00

Minimum number of person 2

Subtask elapsed time 8.00

Skills AIRFRAME

Material necessary to do the job

Kit 536177A07R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

8 EN6115V3A7 7 SCREW

9 ASNA2529-3 39 NUT

10 EN6115V3A6 10 SCREW

12 ASNA2529-6 2 NUT

13 ASNA2001V5-8Y 2 SCREW

14 NAS1726-5E 2 NUT

15 EN6114V5Y8 4 SCREW

16 ASNA2529-5 5 NUT

17 EN6115V3A5 9 SCREW

19 ASNA2050DXJ4020 2 RIVET

21 ASNA2529-4 1 NUT

26 EN6114V6X14 2 SCREW

30 EN6114V4X8 1 SCREW

32 EN6115V3A8 11 SCREW

33 EN6115V3A9 1 SCREW

36 EN6115V3A3 5 SCREW

41 EN6114V5X10 1 SCREW

56 NSA5057-6 4 NUT

104 A5711113120095 1 FOOT

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Wash Primer - Structure 04CMA2 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 437

5

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

SERVICE BULLETIN

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Primer Polyurethane Paint -

Corrosion Inhibiting

04EAC2 As required

Polysulfide Sealant -

General Purpose Brushable

06AAA1 As required

Polysulfide Sealant - Fuel

Tank Brushable

06ABA1 As required

Polysulfide Sealant - Fuel

Tank Fillet

06ABB1 As required

References

Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001

Structural Repair Manual (SRM) 51-40-00

51-40-20

51-40-30

51-40-40

Fig. A-FEAAA

Replacement of the Frame foot FR43,

LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Fig. A-FPAAA

Removal/Installation of the Gussets at

FR43, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

(a) Install and drill all the parts.

Refer to Fig. A-FEAAA

In accordance with SRM 51-40-40

1 Put all the parts in position as shown on Fig. A-FEAAA.

1 Frame foot A5711113120095 Item 104

1 Stiffener Item (58) Retained at

removal

1 Shim Item (70) Retained at

removal

1 Splice Item (72) Retained at

removal

NOTE: If necessary, rework the upper and side surfaces of the Frame

foot with a maximum of 0.5 mm (0.020 in.) as shown on Fig.

A-FEAAA Sheet 03.

NOTE: Between parts apply:

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 438

5

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

SERVICE BULLETIN

Polysulfide Sealant

- Fuel Tank Fillet

06ABB1 As required

2 Drill the holes of the Frame foot H121 to H136, H140 to H149 and H152 to

H157 to the diameter given on Fig. A-FEAAA Sheet 03 and Fig. A-FEAAA

Sheet 04.

3 Drill the holes of the stiffener H168 and H169 to the diameter given on Fig. AFEAAA Sheet 04.

4 Drill the holes of the splice H137 to H139 and H158 to H167 to the diameter

given on Fig. A-FEAAA Sheet 04.

(b) Cut-out the Frame foot Item 104 as shown on Fig. A-FEAAA Sheet 03.

Protect the cut-out with:

Wash Primer -

Structure

04CMA2 As required

Primer

Polyurethane Paint

- Corrosion

Inhibiting

04EAC2 As required

(c) Install the fasteners.

Refer to Fig. A-FEAAA

In accordance with SRM 51-40-00, SRM 51-40-20 and SRM 51-40-30

Refer to AMM 20-21-12, Page Block 001

1 Install the fasteners of the Frame foot H121 to H136, H140 to H149 and H152

to H157:

Refer to Fig. A-FEAAA Sheet 03 and Fig. A-FEAAA Sheet 04

5 Screw EN6115V3A7 Item 8

10 Screw EN6115V3A6 Item 10

2 Screw ASNA2001V5-8Y Item 13

4 Screw EN6114V5Y8 Item 15

5 Screw EN6115V3A5 Item 17

5 Screw EN6115V3A8 Item 32

5 Screw EN6115V3A3 Item 36

26 Nut ASNA2529-3 Item 9

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 439

5

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

SERVICE BULLETIN

2 Nut NAS1726-5E Item 14

4 Nut ASNA2529-5 Item 16

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

2 Install the four upper fasteners of the Frame foot:

Refer to Fig. A-FEAAA Sheet 02

4 Bolt Item (55) Retained at

removal

4 Nut NSA5057-6 Item 56

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

3 Install the fasteners of the stiffener at STGR 36 H168 and H169:

Refer to Fig. A-FEAAA Sheet 04

2 Rivet ASNA2050DXJ4020 Item 19

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 440

5

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

SERVICE BULLETIN

4 Install the fasteners of the splice H137 to H139 and H158 to H167:

Refer to Fig. A-FEAAA Sheet 05

2 Screw EN6115V3A7 Item 8

4 Screw EN6115V3A5 Item 17

6 Screw EN6115V3A8 Item 32

1 Screw EN6115V3A9 Item 33

13 Nut ASNA2529-3 Item 9

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

5 Do a sealant bead around the parts with:

Polysulfide Sealant

- Fuel Tank Fillet

06ABB1 As required

(d) Install the Gussets at Frame 43, LH side.

Refer to Fig. A-FPAAA

In accordance with SRM 51-40-20, SRM 51-40-00, SRM 51-40-30 and SRM

51-40-40

Refer to AMM 20-21-12, Page Block 001

1 Put the gussets in position as shown on Fig. A-FPAAA Sheet 02 and Fig. AFPAAA Sheet 03.

1 Gusset Item (128) Retained at

removal

1 Gusset Item (130) Retained at

removal

NOTE: Between the Frame foot and the aft gusset, the distance must

be 2 times the thickness of the gusset.

NOTE: Between the Frame foot and the FWD gusset, the distance

must be 1.3 times the thickness of the gusset.

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 441

5

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

SERVICE BULLETIN

2 Drill holes H150 and H151 to the diameter given on Fig. A-FPAAA Sheet 03.

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

4 Install:

1 Gusset Item (128) Retained at

removal

1 Gusset Item (130) Retained at

removal

2 Screw EN6114V6X14 Item 26

1 Screw EN6114V4X8 Item 30

1 Screw EN6114V5X10 Item 41

2 Nut ASNA2529-6 Item 12

1 Nut ASNA2529-5 Item 16

1 Nut ASNA2529-4 Item 21

(25) Subtask 536177-831-025-001 - Depending on Inspection results, if removed, install

the Fasteners at FR43, LH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 43

Manpower Resources

Manhours 6.00

Minimum number of person 2

Subtask elapsed time 3.00

Skills AIRFRAME

Material necessary to do the job

Component COMPA03

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

9 ASNA2529-3 24 NUT

47 EN6114V3X6 24 SCREW

90 ASNA2019-56-25 24 RIVET

92 EN6080D6X-32 16 RIVET

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 442

5

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

SERVICE BULLETIN

NOTE: The components listed above are only necessary if crack is found on a

Frame foot. The quantity of these items are to be ordered as required.

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant - Fuel

Tank Brushable

06ABA1 As required

References

Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001

Structural Repair Manual (SRM) 51-24-00

51-40-00

51-40-20

51-40-30

Fig. A-FVAAA

Removal/Installation of the Fasteners

from FR41 to FR46, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

(a) If removed, install the fasteners at Frame 43, LH side.

Refer to Fig. A-FVAAA

In accordance with SRM 51-40-20, SRM 51-24-00, SRM 51-40-00 and SRM

51-40-30

Refer to AMM 20-21-12, Page Block 001

1 Install:

16 Rivet EN6080D6X-32 Item 92

And:

24 Rivet ASNA2019-56-25 Item 90

or

24 Screw EN6114V3X6 Item 47

24 Nut ASNA2529-3 Item 9

NOTE: Protect the fasteners with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 443

5

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

SERVICE BULLETIN

(26) Subtask 536177-831-026-001 - Depending on Inspection results, if necessary,

remove the Fasteners from FR43, RH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 43

Manpower Resources

Manhours 4.00

Minimum number of person 2

Subtask elapsed time 2.00

Skills AIRFRAME

References

Structural Repair Manual (SRM) 51-40-20

Fig. A-FVAAA

Removal/Installation of the Fasteners

from FR41 to FR46, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

(a) If necessary, to ease the replacement of the Frame foot, remove fasteners from

Frame 43, RH side.

Refer to Fig. A-FVAAA

In accordance with SRM 51-40-20

1 Remove:

16 Rivet Item (19) Discard

And:

24 Rivet Item (5) Discard

or

24 Bolt Item (3) Discard

24 Nut Item (4) Discard

(27) Subtask 536177-831-027-001 - Depending on Inspection results, remove the

Gussets from FR43, RH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 43

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 444

5

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

SERVICE BULLETIN

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills AIRFRAME

References

Structural Repair Manual (SRM) 51-40-20

Fig. A-FPAAA

Removal/Installation of the Gussets at

FR43, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

(a) Remove the Gussets from Frame 43, RH side.

Refer to Fig. A-FPAAA

In accordance with SRM 51-40-20

1 Remove:

1 Gusset Item (129) Retain

1 Gusset Item (131) Retain

attached with:

4 Screw Item (3) Discard

4 Nut Item (4) Discard

(28) Subtask 536177-831-028-001 - Depending on Inspection results, remove the Frame

Foot from FR43, RH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 43

Manpower Resources

Manhours 16.00

Minimum number of person 2

Subtask elapsed time 8.00

Skills AIRFRAME

References

Structural Repair Manual (SRM) 51-40-20

Fig. A-FEAAA

Replacement of the Frame foot FR43,

LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 445

5

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

SERVICE BULLETIN

(a) Remove the Frame foot from Frame 43, RH side.

Refer to Fig. A-FEAAA

In accordance with SRM 51-40-20

1 Remove:

1 Frame foot Item (105) Discard

1 Stiffener Item (57) Retain

1 Shim Item (70) Retain

1 Splice Item (71) Retain

4 Bolt Item (55) Retain

4 Nut Item (56) Discard

16 Pin Item (1) Discard

16 Collar Item (2) Discard

31 Bolt Item (3) Discard

31 Nut Item (4) Discard

2 Rivet Item (5) Discard

(29) Subtask 536177-831-029-001 - Depending on Inspection results, install an identical

Frame Foot at FR43, RH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 43

Manpower Resources

Manhours 16.00

Minimum number of person 2

Subtask elapsed time 8.00

Skills AIRFRAME

Material necessary to do the job

Kit 536177A25R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

8 EN6115V3A7 7 SCREW

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 446

5

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

SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

9 ASNA2529-3 39 NUT

10 EN6115V3A6 10 SCREW

12 ASNA2529-6 2 NUT

13 ASNA2001V5-8Y 2 SCREW

14 NAS1726-5E 2 NUT

15 EN6114V5Y8 4 SCREW

16 ASNA2529-5 5 NUT

17 EN6115V3A5 9 SCREW

19 ASNA2050DXJ4020 2 RIVET

21 ASNA2529-4 1 NUT

26 EN6114V6X14 2 SCREW

30 EN6114V4X8 1 SCREW

32 EN6115V3A8 11 SCREW

33 EN6115V3A9 1 SCREW

36 EN6115V3A3 5 SCREW

41 EN6114V5X10 1 SCREW

56 NSA5057-6 4 NUT

105 A5711113120195 1 FOOT

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Wash Primer - Structure 04CMA2 As required

Primer Polyurethane Paint -

Corrosion Inhibiting

04EAC2 As required

Polysulfide Sealant -

General Purpose Brushable

06AAA1 As required

Polysulfide Sealant - Fuel

Tank Brushable

06ABA1 As required

Polysulfide Sealant - Fuel

Tank Fillet

06ABB1 As required

References

Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001

Structural Repair Manual (SRM) 51-40-00

51-40-20

51-40-30

51-40-40

Fig. A-FEAAA

Replacement of the Frame foot FR43,

LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Fig. A-FPAAA

Removal/Installation of the Gussets at

FR43, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 447

5

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

SERVICE BULLETIN

(a) Install and drill all the parts.

Refer to Fig. A-FEAAA

In accordance with SRM 51-40-40

1 Put all the parts in position as shown on Fig. A-FEAAA.

1 Frame foot A5711113120195 Item 105

1 Stiffener Item (57) Retained at

removal

1 Shim Item (70) Retained at

removal

1 Splice Item (71) Retained at

removal

NOTE: If necessary, rework the upper and side surfaces of the Frame

foot with a maximum of 0.5 mm (0.020 in.) as shown on Fig.

A-FEAAA Sheet 03.

NOTE: Between parts apply:

Polysulfide Sealant

- Fuel Tank Fillet

06ABB1 As required

2 Drill the holes of the Frame foot H121 to H136, H140 to H149 and H152 to

H157 to the diameter given on Fig. A-FEAAA Sheet 03 and Fig. A-FEAAA

Sheet 04.

3 Drill the holes of the stiffener H168 and H169 to the diameter given on Fig. AFEAAA Sheet 04.

4 Drill the holes of the splice H137 to H139 and H158 to H167 to the diameter

given on Fig. A-FEAAA Sheet 04.

(b) Cut-out the Frame foot Item 104 as shown on Fig. A-FEAAA Sheet 03.

Protect the cut-out with:

Wash Primer -

Structure

04CMA2 As required

Primer

Polyurethane Paint

- Corrosion

Inhibiting

04EAC2 As required

(c) Install the fasteners.

Refer to Fig. A-FEAAA

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 448

5

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

SERVICE BULLETIN

In accordance with SRM 51-40-00, SRM 51-40-20 and SRM 51-40-30

Refer to AMM 20-21-12, Page Block 001

1 Install the fasteners of the Frame foot H121 to H136, H140 to H149 and H152

to H157:

Refer to Fig. A-FEAAA Sheet 03 and Fig. A-FEAAA Sheet 04

5 Screw EN6115V3A7 Item 8

10 Screw EN6115V3A6 Item 10

2 Screw ASNA2001V5-8Y Item 13

4 Screw EN6114V5Y8 Item 15

5 Screw EN6115V3A5 Item 17

5 Screw EN6115V3A8 Item 32

5 Screw EN6115V3A3 Item 36

26 Nut ASNA2529-3 Item 9

2 Nut NAS1726-5E Item 14

4 Nut ASNA2529-5 Item 16

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

2 Install the four upper fasteners of the Frame foot:

Refer to Fig. A-FEAAA Sheet 02

4 Bolt Item (55) Retained at

removal

4 Nut NSA5057-6 Item 56

NOTE: Wet install the fasteners with:

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 449

5

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

SERVICE BULLETIN

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

3 Install the fasteners of the stiffener at STGR 36 H168 and H169:

Refer to Fig. A-FEAAA Sheet 04

2 Rivet ASNA2050DXJ4020 Item 19

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

4 Install the fasteners of the splice H137 to H139 and H158 to H167:

Refer to Fig. A-FEAAA Sheet 05

2 Screw EN6115V3A7 Item 8

4 Screw EN6115V3A5 Item 17

6 Screw EN6115V3A8 Item 32

1 Screw EN6115V3A9 Item 33

13 Nut ASNA2529-3 Item 9

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 450

5

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

SERVICE BULLETIN

5 Do a sealant bead around the parts with:

Polysulfide Sealant

- Fuel Tank Fillet

06ABB1 As required

(d) Install the Gussets at Frame 43, LH side.

Refer to Fig. A-FPAAA

In accordance with SRM 51-40-20, SRM 51-40-00, SRM 51-40-30 and SRM

51-40-40

Refer to AMM 20-21-12, Page Block 001

1 Put the gussets in position as shown on Fig. A-FPAAA Sheet 02 and Fig. AFPAAA Sheet 03.

1 Gusset Item (129) Retained at

removal

1 Gusset Item (131) Retained at

removal

NOTE: Between the Frame foot and the aft gusset, the distance must

be 2 times the thickness of the gusset.

NOTE: Between the Frame foot and the FWD gusset, the distance

must be 1.3 times the thickness of the gusset.

2 Drill holes H150 and H151 to the diameter given on Fig. A-FPAAA Sheet 03.

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

4 Install:

1 Gusset Item (129) Retained at

removal

1 Gusset Item (131) Retained at

removal

2 Screw EN6114V6X14 Item 26

1 Screw EN6114V4X8 Item 30

1 Screw EN6114V5X10 Item 41

2 Nut ASNA2529-6 Item 12

1 Nut ASNA2529-5 Item 16

1 Nut ASNA2529-4 Item 21

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 451

5

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

SERVICE BULLETIN

(30) Subtask 536177-831-030-001 - Depending on Inspection results, if removed, install

the Fasteners at FR43, RH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 43

Manpower Resources

Manhours 6.00

Minimum number of person 2

Subtask elapsed time 3.00

Skills AIRFRAME

Material necessary to do the job

Component COMPA03

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

9 ASNA2529-3 24 NUT

47 EN6114V3X6 24 SCREW

90 ASNA2019-56-25 24 RIVET

92 EN6080D6X-32 16 RIVET

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

NOTE: The components listed above are only necessary if crack is found on a

Frame foot. The quantity of these items are to be ordered as required.

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant - Fuel

Tank Brushable

06ABA1 As required

References

Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001

Structural Repair Manual (SRM) 51-24-00

51-40-00

51-40-20

51-40-30

Fig. A-FVAAA

Removal/Installation of the Fasteners

from FR41 to FR46, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 452

5

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

SERVICE BULLETIN

(a) If removed, install the fasteners at Frame 43, RH side.

Refer to Fig. A-FVAAA

In accordance with SRM 51-40-20, SRM 51-24-00, SRM 51-40-00 and SRM

51-40-30

Refer to AMM 20-21-12, Page Block 001

1 Install:

16 Rivet EN6080D6X-32 Item 92

And:

24 Rivet ASNA2019-56-25 Item 90

or

24 Screw EN6114V3X6 Item 47

24 Nut ASNA2529-3 Item 9

NOTE: Protect the fasteners with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

(31) Subtask 536177-831-031-001 - Depending on Inspection results, if necessary,

remove the Fasteners from FR44, LH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 44

Manpower Resources

Manhours 4.00

Minimum number of person 2

Subtask elapsed time 2.00

Skills AIRFRAME

References

Structural Repair Manual (SRM) 51-40-20

Fig. A-FVAAA

Removal/Installation of the Fasteners

from FR41 to FR46, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 453

5

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

SERVICE BULLETIN

(a) If necessary, to ease the replacement of the Frame foot, remove fasteners from

Frame 44, LH side.

Refer to Fig. A-FVAAA

In accordance with SRM 51-40-20

1 Remove:

16 Rivet Item (19) Discard

And:

24 Rivet Item (5) Discard

or

24 Bolt Item (3) Discard

24 Nut Item (4) Discard

(32) Subtask 536177-831-032-001 - Depending on Inspection results, remove the

Gussets from FR44, LH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 44

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills AIRFRAME

References

Structural Repair Manual (SRM) 51-40-20

Fig. A-FQAAA

Removal/Installation of the Gussets at

FR44, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

(a) Remove the Gussets from Frame 44, LH side.

Refer to Fig. A-FQAAA

In accordance with SRM 51-40-20

1 Remove:

1 Gusset Item (132) Retain

1 Gusset Item (134) Retain

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 454

5

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

SERVICE BULLETIN

attached with:

4 Screw Item (3) Discard

4 Nut Item (4) Discard

(33) Subtask 536177-831-033-001 - Depending on Inspection results, remove the Frame

Foot from FR44, LH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 44

Manpower Resources

Manhours 16.00

Minimum number of person 2

Subtask elapsed time 8.00

Skills AIRFRAME

References

Structural Repair Manual (SRM) 51-40-20

Fig. A-FGAAA

Replacement of the Frame foot FR44,

LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

(a) Remove the Frame foot from Frame 44, LH side.

Refer to Fig. A-FGAAA

In accordance with SRM 51-40-20

1 Remove:

1 Frame foot Item (106) Discard

1 Stiffener Item (58) Retain

1 Splice Item (74) Retain

1 Shim Item (73) Retain

4 Bolt Item (55) Retain

4 Nut Item (56) Discard

15 Pin Item (1) Discard

15 Collar Item (2) Discard

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 455

5

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

SERVICE BULLETIN

26 Bolt Item (3) Discard

26 Nut Item (4) Discard

2 Rivet Item (5) Discard

(34) Subtask 536177-831-034-001 - Depending on Inspection results, install an identical

Frame Foot at FR44, LH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 44

Manpower Resources

Manhours 16.00

Minimum number of person 2

Subtask elapsed time 8.00

Skills AIRFRAME

Material necessary to do the job

Kit 536177A10R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

8 EN6115V3A7 11 SCREW

9 ASNA2529-3 35 NUT

10 EN6115V3A6 12 SCREW

12 ASNA2529-6 2 NUT

13 ASNA2001V5-8Y 2 SCREW

14 NAS1726-5E 2 NUT

15 EN6114V5Y8 2 SCREW

16 ASNA2529-5 4 NUT

17 EN6115V3A5 9 SCREW

18 EN6115V3A4 2 SCREW

19 ASNA2050DXJ4020 2 RIVET

26 EN6114V6X14 2 SCREW

28 EN6114V5X8 1 SCREW

36 EN6115V3A3 1 SCREW

41 EN6114V5X10 1 SCREW

56 NSA5057-6 4 NUT

106 A5711113220095 1 FOOT

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Wash Primer - Structure 04CMA2 As required

Primer Polyurethane Paint -

Corrosion Inhibiting

04EAC2 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 456

5

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

SERVICE BULLETIN

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant -

General Purpose Brushable

06AAA1 As required

Polysulfide Sealant - Fuel

Tank Brushable

06ABA1 As required

Polysulfide Sealant - Fuel

Tank Fillet

06ABB1 As required

References

Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001

Structural Repair Manual (SRM) 51-40-00

51-40-20

51-40-30

51-40-40

Fig. A-FQAAA

Removal/Installation of the Gussets at

FR44, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Fig. A-FGAAA

Replacement of the Frame foot FR44,

LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

(a) Install and drill all the parts.

Refer to Fig. A-FGAAA

In accordance with SRM 51-40-40

1 Put all the parts in position as shown on Fig. A-FGAAA.

1 Frame foot A5711113220095 Item 106

1 Stiffener Item (58) Retained at

removal

1 Splice Item (74) Retained at

removal

1 Shim Item (73) Retained at

removal

NOTE: If necessary, rework the upper and side surfaces of the Frame

foot with a maximum of 0.5 mm (0.020 in.) as shown on Fig.

A-FGAAA Sheet 03.

NOTE: Between parts apply:

Polysulfide Sealant

- Fuel Tank Fillet

06ABB1 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 457

5

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

SERVICE BULLETIN

2 Drill the holes of the Frame foot H180 to H202 and H205 to H208 to the

diameter given on Fig. A-FGAAA Sheet 03 and Fig. A-FGAAA Sheet 04.

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

4 Drill the holes of the splice H209 to H220 to the diameter given on Fig. AFGAAA Sheet 05.

(b) Cut-out the Frame foot Item 106 as shown on Fig. A-FGAAA Sheet 03.

Protect the cut-out with:

Wash Primer -

Structure

04CMA2 As required

Primer

Polyurethane Paint

- Corrosion

Inhibiting

04EAC2 As required

(c) Install the fasteners.

Refer to Fig. A-FGAAA

In accordance with SRM 51-40-00, SRM 51-40-20, and SRM 51-40-30

Refer to AMM 20-21-12, Page Block 001

1 Install the fasteners of the Frame foot H180 to H202 and H205 to H208:

Refer to Fig. A-FGAAA Sheet 03 and Fig. A-FGAAA Sheet 04

10 Screw EN6115V3A7 Item 8

12 Screw EN6115V3A6 Item 10

2 Screw ASNA2001V5-8Y Item 13

2 Screw EN6114V5Y8 Item 15

1 Screw EN6115V3A3 Item 36

23 Nut ASNA2529-3 Item 9

2 Nut NAS1726-5E Item 14

2 Nut ASNA2529-5 Item 16

NOTE: For holes H205 to H208, adjust the shims as shown on Fig. AFGAAA Sheet 04.

NOTE: Wet install the fasteners except for holes H203 and H204 with:

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 458

5

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

SERVICE BULLETIN

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

2 Install the four upper fasteners of the Frame foot:

Refer to Fig. A-FGAAA Sheet 02

4 Bolt Item (55) Retained at

removal

4 Nut NSA5057-6 Item 56

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

3 Install the fasteners of the stiffener at STGR 36 H221 and H222:

Refer to Fig. A-FGAAA Sheet 03

2 Rivet ASNA2050DXJ4020 Item 19

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

4 Install the fasteners of the splice H209 to H220:

Refer to Fig. A-FGAAA Sheet 05

1 Screw EN6115V3A7 Item 8

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 459

5

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

SERVICE BULLETIN

9 Screw EN6115V3A5 Item 17

2 Screw EN6115V3A4 Item 18

12 Nut ASNA2529-3 Item 9

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

5 Do a sealant bead around the parts with:

Polysulfide Sealant

- Fuel Tank Fillet

06ABB1 As required

(d) Install the Gussets at Frame 44, LH side.

Refer to Fig. A-FQAAA

In accordance with SRM 51-40-20, SRM 51-40-00 and SRM 51-40-30

Refer to AMM 20-21-12, Page Block 001

1 Put the gussets in position as shown on Fig. A-FQAAA.

1 Gusset Item (132) Retained at

removal

1 Gusset Item (134) Retained at

removal

NOTE: Between the Frame foot and the aft gusset, the distance must

be 2 times the thickness of the gusset.

NOTE: Between the Frame foot and the FWD gusset, the distance

must be 1.3 times the thickness of the gusset.

2 Drill holes H203 and H204 to the diameter given on Fig. A-FQAAA Sheet 03.

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

4 Install:

1 Gusset Item (132) Retained at

removal

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 460

5

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

SERVICE BULLETIN

1 Gusset Item (134) Retained at

removal

2 Screw EN6114V6X14 Item 26

1 Screw EN6114V5X8 Item 28

1 Screw EN6114V5X10 Item 41

2 Nut ASNA2529-6 Item 12

2 Nut ASNA2529-5 Item 16

(35) Subtask 536177-831-035-001 - Depending on Inspection results, if removed, install

the Fasteners at FR44, LH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 44

Manpower Resources

Manhours 6.00

Minimum number of person 2

Subtask elapsed time 3.00

Skills AIRFRAME

Material necessary to do the job

Component COMPA02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

9 ASNA2529-3 24 NUT

90 ASNA2019-56-25 24 RIVET

91 EN6114V3X5 24 SCREW

92 EN6080D6X-32 16 RIVET

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

NOTE: The components listed above are only necessary if crack is found on a

Frame foot. The quantity of these items are to be ordered as required.

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant - Fuel

Tank Brushable

06ABA1 As required

References

Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 461

5

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

SERVICE BULLETIN

References

Structural Repair Manual (SRM) 51-24-00

51-40-00

51-40-20

51-40-30

Fig. A-FVAAA

Removal/Installation of the Fasteners

from FR41 to FR46, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

(a) If removed, install the fasteners at Frame 44, LH side.

Refer to Fig. A-FVAAA

In accordance with SRM 51-40-20, SRM 51-24-00, SRM 51-40-00 and SRM

51-40-30

Refer to AMM 20-21-12, Page Block 001

1 Install:

16 Rivet EN6080D6X-32 Item 92

And:

24 Rivet ASNA2019-56-25 Item 90

or

24 Screw EN6114V3X5 Item 91

24 Nut ASNA2529-3 Item 9

NOTE: Protect the fasteners with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

(36) Subtask 536177-831-036-001 - Depending on Inspection results, if necessary,

remove the Fasteners from FR44, RH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 44

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 462

5

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

SERVICE BULLETIN

Manpower Resources

Manhours 4.00

Minimum number of person 2

Subtask elapsed time 2.00

Skills AIRFRAME

References

Structural Repair Manual (SRM) 51-40-20

Fig. A-FVAAA

Removal/Installation of the Fasteners

from FR41 to FR46, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

(a) If necessary, to ease the replacement of the Frame foot, remove fasteners from

Frame 44, RH side.

Refer to Fig. A-FVAAA

In accordance with SRM 51-40-20

1 Remove:

16 Rivet Item (19) Discard

And:

24 Rivet Item (5) Discard

or

24 Bolt Item (3) Discard

24 Nut Item (4) Discard

(37) Subtask 536177-831-037-001 - Depending on Inspection results, remove the

Gussets from FR44, RH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 44

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills AIRFRAME

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 463

5

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

SERVICE BULLETIN

References

Structural Repair Manual (SRM) 51-40-20

Fig. A-FQAAA

Removal/Installation of the Gussets at

FR44, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

(a) Remove the Gussets from Frame 44, RH side.

Refer to Fig. A-FQAAA

In accordance with SRM 51-40-20

1 Remove:

1 Gusset Item (133) Retain

1 Gusset Item (135) Retain

attached with:

4 Screw Item (3) Discard

4 Nut Item (4) Discard

(38) Subtask 536177-831-038-001 - Depending on Inspection results, remove the Frame

Foot from FR44, RH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 44

Manpower Resources

Manhours 16.00

Minimum number of person 2

Subtask elapsed time 8.00

Skills AIRFRAME

References

Structural Repair Manual (SRM) 51-40-20

Fig. A-FGAAA

Replacement of the Frame foot FR44,

LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

(a) Remove the Frame foot from Frame 44, RH side.

Refer to Fig. A-FGAAA

In accordance with SRM 51-40-20

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 464

5

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

SERVICE BULLETIN

1 Remove:

1 Frame foot Item (107) Discard

1 Stiffener Item (57) Retain

1 Splice Item (75) Retain

1 Shim Item (73) Retain

4 Bolt Item (55) Retain

4 Nut Item (56) Discard

15 Pin Item (1) Discard

15 Collar Item (2) Discard

26 Bolt Item (3) Discard

26 Nut Item (4) Discard

2 Rivet Item (5) Discard

(39) Subtask 536177-831-039-001 - Depending on Inspection results, install an identical

Frame Foot at FR44, RH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 44

Manpower Resources

Manhours 16.00

Minimum number of person 2

Subtask elapsed time 8.00

Skills AIRFRAME

Material necessary to do the job

Kit 536177A28R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

8 EN6115V3A7 11 SCREW

9 ASNA2529-3 35 NUT

10 EN6115V3A6 12 SCREW

12 ASNA2529-6 2 NUT

13 ASNA2001V5-8Y 2 SCREW

14 NAS1726-5E 2 NUT

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 465

5

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

SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

15 EN6114V5Y8 2 SCREW

16 ASNA2529-5 4 NUT

17 EN6115V3A5 9 SCREW

18 EN6115V3A4 2 SCREW

19 ASNA2050DXJ4020 2 RIVET

26 EN6114V6X14 2 SCREW

28 EN6114V5X8 1 SCREW

36 EN6115V3A3 1 SCREW

41 EN6114V5X10 1 SCREW

56 NSA5057-6 4 NUT

107 A5711113220195 1 FOOT

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Wash Primer - Structure 04CMA2 As required

Primer Polyurethane Paint -

Corrosion Inhibiting

04EAC2 As required

Polysulfide Sealant -

General Purpose Brushable

06AAA1 As required

Polysulfide Sealant - Fuel

Tank Brushable

06ABA1 As required

Polysulfide Sealant - Fuel

Tank Fillet

06ABB1 As required

References

Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001

Structural Repair Manual (SRM) 51-40-00

51-40-20

51-40-30

51-40-40

Fig. A-FGAAA

Replacement of the Frame foot FR44,

LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Fig. A-FQAAA

Removal/Installation of the Gussets at

FR44, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

(a) Install and drill all the parts.

Refer to Fig. A-FGAAA

In accordance with SRM 51-40-40

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 466

5

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

SERVICE BULLETIN

1 Put all the parts in position as shown on Fig. A-FGAAA.

1 Frame foot A5711113220195 Item 107

1 Stiffener Item (57) Retained at

removal

1 Splice Item (75) Retained at

removal

1 Shim Item (73) Retained at

removal

NOTE: If necessary, rework the upper and side surfaces of the Frame

foot with a maximum of 0.5 mm (0.020 in.) as shown on Fig.

A-FGAAA Sheet 03.

NOTE: Between parts apply:

Polysulfide Sealant

- Fuel Tank Fillet

06ABB1 As required

2 Drill the holes of the Frame foot H180 to H202 and H205 to H208 to the

diameter given on Fig. A-FGAAA Sheet 03 and Fig. A-FGAAA Sheet 04.

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

4 Drill the holes of the splice H209 to H220 to the diameter given on Fig. AFGAAA Sheet 05.

(b) Cut-out the Frame foot Item 106 as shown on Fig. A-FGAAA Sheet 03.

Protect the cut-out with:

Wash Primer -

Structure

04CMA2 As required

Primer

Polyurethane Paint

- Corrosion

Inhibiting

04EAC2 As required

(c) Install the fasteners.

Refer to Fig. A-FGAAA

In accordance with SRM 51-40-00, SRM 51-40-20, and SRM 51-40-30

Refer to AMM 20-21-12, Page Block 001

1 Install the fasteners of the Frame foot H180 to H202 and H205 to H208:

Refer to Fig. A-FGAAA Sheet 03 and Fig. A-FGAAA Sheet 04

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 467

5

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

SERVICE BULLETIN

10 Screw EN6115V3A7 Item 8

12 Screw EN6115V3A6 Item 10

2 Screw ASNA2001V5-8Y Item 13

2 Screw EN6114V5Y8 Item 15

1 Screw EN6115V3A3 Item 36

23 Nut ASNA2529-3 Item 9

2 Nut NAS1726-5E Item 14

2 Nut ASNA2529-5 Item 16

NOTE: For holes H205 to H208, adjust the shims as shown on Fig. AFGAAA Sheet 04.

NOTE: Wet install the fasteners except for holes H203 and H204 with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

2 Install the four upper fasteners of the Frame foot:

Refer to Fig. A-FGAAA Sheet 02

4 Bolt Item (55) Retained at

removal

4 Nut NSA5057-6 Item 56

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 468

5

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

SERVICE BULLETIN

3 Install the fasteners of the stiffener at STGR 36 H221 and H222:

Refer to Fig. A-FGAAA Sheet 03

2 Rivet ASNA2050DXJ4020 Item 19

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

4 Install the fasteners of the splice H209 to H220:

Refer to Fig. A-FGAAA Sheet 05

1 Screw EN6115V3A7 Item 8

9 Screw EN6115V3A5 Item 17

2 Screw EN6115V3A4 Item 18

12 Nut ASNA2529-3 Item 9

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

5 Do a sealant bead around the parts with:

Polysulfide Sealant

- Fuel Tank Fillet

06ABB1 As required

(d) Install the Gussets at Frame 44, LH side.

Refer to Fig. A-FQAAA

In accordance with SRM 51-40-20, SRM 51-40-00 and SRM 51-40-30

Refer to AMM 20-21-12, Page Block 001

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 469

5

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

SERVICE BULLETIN

1 Put the gussets in position as shown on Fig. A-FQAAA.

1 Gusset Item (133) Retained at

removal

1 Gusset Item (135) Retained at

removal

NOTE: Between the Frame foot and the aft gusset, the distance must

be 2 times the thickness of the gusset.

NOTE: Between the Frame foot and the FWD gusset, the distance

must be 1.3 times the thickness of the gusset.

2 Drill holes H203 and H204 to the diameter given on Fig. A-FQAAA Sheet 03.

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

4 Install:

1 Gusset Item (133) Retained at

removal

1 Gusset Item (135) Retained at

removal

2 Screw EN6114V6X14 Item 26

1 Screw EN6114V5X8 Item 28

1 Screw EN6114V5X10 Item 41

2 Nut ASNA2529-6 Item 12

2 Nut ASNA2529-5 Item 16

(40) Subtask 536177-831-040-001 - Depending on Inspection results, if removed, install

the Fasteners at FR44, RH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 44

Manpower Resources

Manhours 6.00

Minimum number of person 2

Subtask elapsed time 3.00

Skills AIRFRAME

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 470

5

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

SERVICE BULLETIN

Material necessary to do the job

Component COMPA02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

9 ASNA2529-3 24 NUT

90 ASNA2019-56-25 24 RIVET

91 EN6114V3X5 24 SCREW

92 EN6080D6X-32 16 RIVET

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

NOTE: The components listed above are only necessary if crack is found on a

Frame foot. The quantity of these items are to be ordered as required.

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant - Fuel

Tank Brushable

06ABA1 As required

References

Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001

Structural Repair Manual (SRM) 51-24-00

51-40-00

51-40-20

51-40-30

Fig. A-FVAAA

Removal/Installation of the Fasteners

from FR41 to FR46, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

(a) If removed, install the fasteners at Frame 44, RH side.

Refer to Fig. A-FVAAA

In accordance with SRM 51-40-20, SRM 51-24-00, SRM 51-40-00 and SRM

51-40-30

Refer to AMM 20-21-12, Page Block 001

1 Install:

16 Rivet EN6080D6X-32 Item 92

And:

24 Rivet ASNA2019-56-25 Item 90

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 471

5

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

SERVICE BULLETIN

or

24 Screw EN6114V3X5 Item 91

24 Nut ASNA2529-3 Item 9

NOTE: Protect the fasteners with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

(41) Subtask 536177-831-041-001 - Depending on Inspection results, if necessary,

remove the Fasteners from FR45, LH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 45

Manpower Resources

Manhours 4.00

Minimum number of person 2

Subtask elapsed time 2.00

Skills AIRFRAME

References

Structural Repair Manual (SRM) 51-40-20

Fig. A-FVAAA

Removal/Installation of the Fasteners

from FR41 to FR46, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

(a) If necessary, to ease the replacement of the Frame foot, remove fasteners from

Frame 45, LH side.

Refer to Fig. A-FVAAA

In accordance with SRM 51-40-20

1 Remove:

20 Rivet Item (19) Discard

And:

32 Rivet Item (5) Discard

or

32 Bolt Item (3) Discard

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 472

5

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

SERVICE BULLETIN

32 Nut Item (4) Discard

(42) Subtask 536177-831-042-001 - Depending on Inspection results, remove the

Gussets from FR45, LH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 45

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills AIRFRAME

References

Structural Repair Manual (SRM) 51-40-20

Fig. A-FTAAA

Removal/Installation of the Gussets at

FR45, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

(a) Remove the Gussets from Frame 45, LH side.

Refer to Fig. A-FTAAA

In accordance with SRM 51-40-20

1 Remove:

1 Gusset Item (136) Retain

1 Gusset Item (138) Retain

attached with:

4 Screw Item (3) Discard

4 Nut Item (4) Discard

(43) Subtask 536177-831-043-001 - Depending on Inspection results, remove the Frame

Foot from FR45, LH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 45

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 473

5

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

SERVICE BULLETIN

Manpower Resources

Manhours 16.00

Minimum number of person 2

Subtask elapsed time 8.00

Skills AIRFRAME

References

Structural Repair Manual (SRM) 51-40-20

Fig. A-FJAAA

Replacement of the Frame foot FR45,

LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

(a) Remove the Frame foot from Frame 45, LH side.

Refer to Fig. A-FJAAA

In accordance with SRM 51-40-20

1 Remove:

1 Frame foot Item (108) Discard

2 Stiffener Item (58) Retain

1 Splice Item (72) Retain

1 Doubler Item (77) Retain

1 Shim Item (78) Retain

23 Pin Item (1) Discard

23 Collar Item (2) Discard

4 Rivet Item (19) Discard

22 Screw Item (3) Discard

22 Nut Item (4) Discard

And:

4 Screw Item (55) Retain

4 Nut Item (56) Discard

or

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 474

5

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

SERVICE BULLETIN

4 Nut Item (76) Discard

And:

7 Rivet Item (5) Discard

or

7 Screw Item (93) Discard

7 Nut Item (94) Discard

And if installed, remove:

1 Bracket Item (79) Retain

(44) Subtask 536177-831-044-001 - Depending on Inspection results, install an identical

Frame Foot at FR45, LH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 145

Manpower Resources

Manhours 16.00

Minimum number of person 2

Subtask elapsed time 8.00

Skills AIRFRAME

Material necessary to do the job

Kit 536177A13R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

8 EN6115V3A7 4 SCREW

9 ASNA2529-3 48 NUT

10 EN6115V3A6 7 SCREW

12 ASNA2529-6 2 NUT

16 ASNA2529-5 2 NUT

17 EN6115V3A5 3 SCREW

19 ASNA2050DXJ4020 4 RIVET

26 EN6114V6X14 2 SCREW

28 EN6114V5X8 1 SCREW

32 EN6115V3A8 7 SCREW

33 EN6115V3A9 17 SCREW

41 EN6114V5X10 1 SCREW

42 EN6114V3A6 1 SCREW

43 EN6115V3A10 2 SCREW

44 EN6115V3A11 7 SCREW

45 ASNA2001V6-8Y 2 SCREW

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 475

5

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

SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

46 NAS1726-6E 2 NUT

56 NSA5057-6 4 NUT

76 NSA5057-7 4 NUT

108 A5711113320095 1 FOOT

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Wash Primer - Structure 04CMA2 As required

Primer Polyurethane Paint -

Corrosion Inhibiting

04EAC2 As required

Polysulfide Sealant -

General Purpose Brushable

06AAA1 As required

Polysulfide Sealant - Fuel

Tank Brushable

06ABA1 As required

Polysulfide Sealant - Fuel

Tank Fillet

06ABB1 As required

References

Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001

Structural Repair Manual (SRM) 51-40-00

51-40-20

51-40-30

51-40-40

Fig. A-FJAAA

Replacement of the Frame foot FR45,

LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Fig. A-FTAAA

Removal/Installation of the Gussets at

FR45, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

(a) Install and drill all the parts.

Refer to Fig. A-FJAAA

In accordance with SRM 51-40-40

1 Put all the parts in position as shown on Fig. A-FJAAA.

1 Frame foot A5711113320095 Item 108

2 Stiffener Item (58) Retained at

removal

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 476

5

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

SERVICE BULLETIN

1 Splice Item (72) Retained at

removal

1 Doubler Item (77) Retained at

removal

1 Shim Item (78) Retained at

removal

NOTE: If necessary, rework the upper and side surfaces of the Frame

foot with a maximum of 0.5 mm (0.020 in.) as shown on Fig.

A-FJAAA Sheet 03.

NOTE: Between parts apply:

Polysulfide Sealant

- Fuel Tank Fillet

06ABB1 As required

2 Drill the holes of the Frame foot H231 to H254, H257 to H266 and H271 to

H272 to the diameter given on Fig. A-FJAAA Sheet 03 to Fig. A-FJAAA Sheet

05.

3 Drill the holes of the stiffener at STGR 36 H255 and H256 to the diameter

given on Fig. A-FJAAA Sheet 03.

4 Drill the holes of the stiffener at STGR 37 H267 and H268 to the diameter

given on Fig. A-FJAAA Sheet 05.

5 Drill the holes of the splice H273 to H285 to the diameter given on Fig. AFJAAA Sheet 06.

(b) Cut-out the Frame foot Item 108 as shown on Fig. A-FJAAA Sheet 03.

Protect the cut-out with:

Wash Primer -

Structure

04CMA2 As required

Primer

Polyurethane Paint

- Corrosion

Inhibiting

04EAC2 As required

(c) Install the fasteners.

Refer to Fig. A-FJAAA

In accordance with SRM 51-40-00, SRM 51-40-20 and SRM 51-40-30

Refer to AMM 20-21-12, Page Block 001

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 477

5

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

SERVICE BULLETIN

1 Install the fasteners of the Frame foot H231 to H254, H257 to H266 and H271

to H272:

Refer to Fig. A-FJAAA Sheet 03 to Fig. A-FJAAA Sheet 05

2 Screw EN6115V3A7 Item 8

5 Screw EN6115V3A6 Item 10

1 Screw EN6115V3A5 Item 17

1 Screw EN6115V3A8 Item 32

16 Screw EN6115V3A9 Item 33

1 Screw EN6114V3A6 Item 42

2 Screw EN6115V3A10 Item 43

7 Screw EN6115V3A11 Item 44

2 Screw ASNA2001V6-8Y Item 45

35 Nut ASNA2529-3 Item 9

2 Nut NAS1726-6E Item 46

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

2 Install the four upper fasteners of the Frame foot:

Refer to Fig. A-FJAAA Sheet 02

4 Bolt Item (55) Retained at

removal

4 Nut NSA5057-6 Item 56

or

4 Nut NSA5057-7 Item 76

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 478

5

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

SERVICE BULLETIN

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

3 Install the fasteners of the stiffener at STGR 36 H255 and H256:

Refer to Fig. A-FJAAA Sheet 03

2 Rivet ASNA2050DXJ4020 Item 19

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

4 Install the fasteners of the stiffener at STGR 37 H267 and H268:

Refer to Fig. A-FJAAA Sheet 06

2 Rivet ASNA2050DXJ4020 Item 19

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

5 Install the fasteners of the splice H273 to H285:

Refer to Fig. A-FJAAA Sheet 06

2 Screw EN6115V3A7 Item 8

2 Screw EN6115V3A5 Item 17

6 Screw EN6115V3A8 Item 32

1 Screw EN6115V3A9 Item 33

13 Nut ASNA2529-3 Item 9

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 479

5

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

SERVICE BULLETIN

2 Screw EN6115V3A6 Item 10

And if removed, install:

1 Bracket Item (79) Retained at

removal

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

6 Do a sealant bead around the parts with:

Polysulfide Sealant

- Fuel Tank Fillet

06ABB1 As required

(d) Install the Gussets at Frame 45, LH side.

Refer to Fig. A-FTAAA

In accordance with SRM 51-40-20, SRM 51-40-00, SRM 51-40-30 and SRM

51-40-40

Refer to AMM 20-21-12, Page Block 001

1 Put the gussets in position as shown on Fig. A-FTAAA.

1 Gusset Item (136) Retained at

removal

1 Gusset Item (138) Retained at

removal

NOTE: Between the Frame foot and the aft gusset, the distance must

be 2 times the thickness of the gusset.

NOTE: Between the Frame foot and the FWD gusset, the distance

must be 1.3 times the thickness of the gusset.

2 Drill holes H269 and H270 to the diameter given on Fig. A-FTAAA Sheet 03.

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

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 480

5

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

SERVICE BULLETIN

4 Install:

1 Gusset Item (136) Retained at

removal

1 Gusset Item (138) Retained at

removal

2 Screw EN6114V6X14 Item 26

1 Screw EN6114V5X8 Item 28

1 Screw EN6114V5X10 Item 41

2 Nut ASNA2529-6 Item 12

2 Nut ASNA2529-5 Item 16

(45) Subtask 536177-831-045-001 - Depending on Inspection results, if removed, install

the Fasteners at FR45, LH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 45

Manpower Resources

Manhours 6.00

Minimum number of person 2

Subtask elapsed time 3.00

Skills AIRFRAME

Material necessary to do the job

Component COMPA04

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

9 ASNA2529-3 32 NUT

47 EN6114V3X6 32 SCREW

90 ASNA2019-56-25 32 RIVET

92 EN6080D6X-32 20 RIVET

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

NOTE: The components listed above are only necessary if crack is found on a

Frame foot. The quantity of these items are to be ordered as required.

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 481

5

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

SERVICE BULLETIN

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant - Fuel

Tank Brushable

06ABA1 As required

References

Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001

Structural Repair Manual (SRM) 51-24-00

51-40-00

51-40-20

51-40-30

Fig. A-FVAAA

Removal/Installation of the Fasteners

from FR41 to FR46, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

(a) If removed, install the fasteners at Frame 45, LH side.

Refer to Fig. A-FVAAA

In accordance with SRM 51-40-20, SRM 51-24-00, SRM 51-40-00 and SRM

51-40-30

Refer to AMM 20-21-12, Page Block 001

1 Install:

20 Rivet EN6080D6X-32 Item 92

And:

32 Rivet ASNA2019-56-25 Item 90

or

32 Screw EN6114V3X6 Item 47

32 Nut ASNA2529-3 Item 9

NOTE: Protect the fasteners with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 482

5

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

SERVICE BULLETIN

(46) Subtask 536177-831-046-001 - Depending on Inspection results, if necessary,

remove the Fasteners from FR45, RH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 45

Manpower Resources

Manhours 4.00

Minimum number of person 2

Subtask elapsed time 2.00

Skills AIRFRAME

References

Structural Repair Manual (SRM) 51-40-20

Fig. A-FVAAA

Removal/Installation of the Fasteners

from FR41 to FR46, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

(a) If necessary, to ease the replacement of the Frame foot, remove fasteners from

Frame 45, RH side.

Refer to Fig. A-FVAAA

In accordance with SRM 51-40-20

1 Remove:

20 Rivet Item (19) Discard

And:

32 Rivet Item (5) Discard

or

32 Bolt Item (3) Discard

32 Nut Item (4) Discard

(47) Subtask 536177-831-047-001 - Depending on Inspection results, remove the

Gussets from FR45, RH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 45

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 483

5

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

SERVICE BULLETIN

Manpower Resources

Manhours 1.00

Minimum number of person 2

Subtask elapsed time 1.00

Skills AIRFRAME

References

Structural Repair Manual (SRM) 51-40-20

Fig. A-FTAAA

Removal/Installation of the Gussets at

FR45, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

(a) Remove the Gussets from Frame 45, RH side.

Refer to Fig. A-FTAAA

In accordance with SRM 51-40-20

1 Remove:

1 Gusset Item (137) Retain

1 Gusset Item (139) Retain

attached with:

4 Screw Item (3) Discard

4 Nut Item (4) Discard

(48) Subtask 536177-831-048-001 - Depending on Inspection results, remove the Frame

Foot from FR45, RH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 45

Manpower Resources

Manhours 16.00

Minimum number of person 2

Subtask elapsed time 8.00

Skills AIRFRAME

References

Structural Repair Manual (SRM) 51-40-20

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 484

5

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

SERVICE BULLETIN

References

Fig. A-FJAAA

Replacement of the Frame foot FR45,

LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

(a) Remove the Frame foot from Frame 45, RH side.

Refer to Fig. A-FJAAA

In accordance with SRM 51-40-20

1 Remove:

1 Frame foot Item (109) Discard

2 Stiffener Item (57) Retain

1 Splice Item (71) Retain

1 Doubler Item (77) Retain

1 Shim Item (78) Retain

23 Pin Item (1) Discard

23 Collar Item (2) Discard

4 Rivet Item (19) Discard

22 Screw Item (3) Discard

22 Nut Item (4) Discard

And:

4 Screw Item (55) Retain

4 Nut Item (56) Discard

or

4 Nut Item (76) Discard

And:

7 Rivet Item (5) Discard

or

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 485

5

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

SERVICE BULLETIN

7 Screw Item (93) Discard

7 Nut Item (94) Discard

(49) Subtask 536177-831-049-001 - Depending on Inspection results, install an identical

Frame Foot at FR45, RH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 45

Manpower Resources

Manhours 16.00

Minimum number of person 2

Subtask elapsed time 8.00

Skills AIRFRAME

Material necessary to do the job

Kit 536177A31R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

8 EN6115V3A7 4 SCREW

9 ASNA2529-3 48 NUT

10 EN6115V3A6 5 SCREW

12 ASNA2529-6 2 NUT

16 ASNA2529-5 2 NUT

17 EN6115V3A5 5 SCREW

19 ASNA2050DXJ4020 4 RIVET

26 EN6114V6X14 2 SCREW

28 EN6114V5X8 1 SCREW

32 EN6115V3A8 7 SCREW

33 EN6115V3A9 17 SCREW

41 EN6114V5X10 1 SCREW

42 EN6114V3A6 1 SCREW

43 EN6115V3A10 2 SCREW

44 EN6115V3A11 7 SCREW

45 ASNA2001V6-8Y 2 SCREW

46 NAS1726-6E 2 NUT

56 NSA5057-6 4 NUT

76 NSA5057-7 4 NUT

109 A5711113320195 1 FOOT

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Wash Primer - Structure 04CMA2 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 486

5

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

SERVICE BULLETIN

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Primer Polyurethane Paint -

Corrosion Inhibiting

04EAC2 As required

Polysulfide Sealant -

General Purpose Brushable

06AAA1 As required

Polysulfide Sealant - Fuel

Tank Brushable

06ABA1 As required

Polysulfide Sealant - Fuel

Tank Fillet

06ABB1 As required

References

Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001

Structural Repair Manual (SRM) 51-40-00

51-40-20

51-40-30

51-40-40

Fig. A-FJAAA

Replacement of the Frame foot FR45,

LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Fig. A-FTAAA

Removal/Installation of the Gussets at

FR45, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

(a) Install and drill all the parts.

Refer to Fig. A-FJAAA

In accordance with SRM 51-40-40

1 Put all the parts in position as shown on Fig. A-FJAAA.

1 Frame foot A5711113320195 Item 109

2 Stiffener Item (57) Retained at

removal

1 Splice Item (71) Retained at

removal

1 Doubler Item (77) Retained at

removal

1 Shim Item (78) Retained at

removal

NOTE: If necessary, rework the upper and side surfaces of the Frame

foot with a maximum of 0.5 mm (0.020 in.) as shown on Fig.

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 487

5

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

SERVICE BULLETIN

A-FJAAA Sheet 03.

NOTE: Between parts apply:

Polysulfide Sealant

- Fuel Tank Fillet

06ABB1 As required

2 Drill the holes of the Frame foot H231 to H254, H257 to H266 and H271 to

H272 to the diameter given on Fig. A-FJAAA Sheet 03 to Fig. A-FJAAA Sheet

05.

3 Drill the holes of the stiffener at STGR 36 H255 and H256 to the diameter

given on Fig. A-FJAAA Sheet 03.

4 Drill the holes of the stiffener at STGR 37 H267 and H268 to the diameter

given on Fig. A-FJAAA Sheet 05.

5 Drill the holes of the splice H273 to H285 to the diameter given on Fig. AFJAAA Sheet 06.

(b) Cut-out the Frame foot Item 108 as shown on Fig. A-FJAAA Sheet 03.

Protect the cut-out with:

Wash Primer -

Structure

04CMA2 As required

Primer

Polyurethane Paint

- Corrosion

Inhibiting

04EAC2 As required

(c) Install the fasteners.

Refer to Fig. A-FJAAA

In accordance with SRM 51-40-00, SRM 51-40-20 and SRM 51-40-30

Refer to AMM 20-21-12, Page Block 001

1 Install the fasteners of the Frame foot H231 to H254, H257 to H266 and H271

to H272:

Refer to Fig. A-FJAAA Sheet 03 to Fig. A-FJAAA Sheet 05

2 Screw EN6115V3A7 Item 8

5 Screw EN6115V3A6 Item 10

1 Screw EN6115V3A5 Item 17

1 Screw EN6115V3A8 Item 32

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 488

5

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

SERVICE BULLETIN

16 Screw EN6115V3A9 Item 33

1 Screw EN6114V3A6 Item 42

2 Screw EN6115V3A10 Item 43

7 Screw EN6115V3A11 Item 44

2 Screw ASNA2001V6-8Y Item 45

35 Nut ASNA2529-3 Item 9

2 Nut NAS1726-6E Item 46

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

2 Install the four upper fasteners of the Frame foot:

Refer to Fig. A-FJAAA Sheet 02

4 Bolt Item (55) Retained at

removal

4 Nut NSA5057-6 Item 56

or

4 Nut NSA5057-7 Item 76

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

3 Install the fasteners of the stiffener at STGR 36 H255 and H256:

Refer to Fig. A-FJAAA Sheet 03

2 Rivet ASNA2050DXJ4020 Item 19

NOTE: Wet install the fasteners with:

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 489

5

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

SERVICE BULLETIN

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

4 Install the fasteners of the stiffener at STGR 37 H267 and H268:

Refer to Fig. A-FJAAA Sheet 06

2 Rivet ASNA2050DXJ4020 Item 19

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

5 Install the fasteners of the splice H273 to H285:

Refer to Fig. A-FJAAA Sheet 06

2 Screw EN6115V3A7 Item 8

4 Screw EN6115V3A5 Item 17

6 Screw EN6115V3A8 Item 32

1 Screw EN6115V3A9 Item 33

13 Nut ASNA2529-3 Item 9

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 490

5

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

SERVICE BULLETIN

6 Do a sealant bead around the parts with:

Polysulfide Sealant

- Fuel Tank Fillet

06ABB1 As required

(d) Install the Gussets at Frame 45, LH side.

Refer to Fig. A-FTAAA

In accordance with SRM 51-40-20, SRM 51-40-00, SRM 51-40-30 and SRM

51-40-40

Refer to AMM 20-21-12, Page Block 001

1 Put the gussets in position as shown on Fig. A-FTAAA.

1 Gusset Item (137) Retained at

removal

1 Gusset Item (139) Retained at

removal

NOTE: Between the Frame foot and the aft gusset, the distance must

be 2 times the thickness of the gusset.

NOTE: Between the Frame foot and the FWD gusset, the distance

must be 1.3 times the thickness of the gusset.

2 Drill holes H269 and H270 to the diameter given on Fig. A-FTAAA Sheet 03.

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

4 Install:

1 Gusset Item (137) Retained at

removal

1 Gusset Item (139) Retained at

removal

2 Screw EN6114V6X14 Item 26

1 Screw EN6114V5X8 Item 28

1 Screw EN6114V5X10 Item 41

2 Nut ASNA2529-6 Item 12

2 Nut ASNA2529-5 Item 16

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 491

5

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

SERVICE BULLETIN

(50) Subtask 536177-831-050-001 - Depending on Inspection results, install the

Fasteners at FR45, RH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 45

Manpower Resources

Manhours 6.00

Minimum number of person 2

Subtask elapsed time 3.00

Skills AIRFRAME

Material necessary to do the job

Component COMPA04

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

9 ASNA2529-3 32 NUT

47 EN6114V3X6 32 SCREW

90 ASNA2019-56-25 32 RIVET

92 EN6080D6X-32 20 RIVET

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

NOTE: The components listed above are only necessary if crack is found on a

Frame foot. The quantity of these items are to be ordered as required.

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant - Fuel

Tank Brushable

06ABA1 As required

References

Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001

Structural Repair Manual (SRM) 51-24-00

51-40-00

51-40-20

51-40-30

Fig. A-FVAAA

Removal/Installation of the Fasteners

from FR41 to FR46, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 492

5

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

SERVICE BULLETIN

(a) If removed, install the fasteners at Frame 45, RH side.

Refer to Fig. A-FVAAA

In accordance with SRM 51-40-20, SRM 51-24-00, SRM 51-40-00 and SRM

51-40-30

Refer to AMM 20-21-12, Page Block 001

1 Install:

20 Rivet EN6080D6X-32 Item 92

And:

32 Rivet ASNA2019-56-25 Item 90

or

32 Screw EN6114V3X6 Item 47

32 Nut ASNA2529-3 Item 9

NOTE: Protect the fasteners with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

(51) Subtask 536177-831-051-001 - Depending on Inspection results, if necessary,

remove the Fasteners from FR46, LH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 46

Manpower Resources

Manhours 4.00

Minimum number of person 2

Subtask elapsed time 2.00

Skills AIRFRAME

References

Structural Repair Manual (SRM) 51-40-20

Fig. A-FVAAA

Removal/Installation of the Fasteners

from FR41 to FR46, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 493

5

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

SERVICE BULLETIN

(a) If necessary, to ease the replacement of the Frame foot, remove fasteners from

Frame 46, LH side.

Refer to Fig. A-FVAAA

In accordance with SRM 51-40-20

1 Remove:

16 Rivet Item (19) Discard

And:

24 Rivet Item (5) Discard

or

24 Bolt Item (3) Discard

24 Nut Item (4) Discard

(52) Subtask 536177-831-052-001 - Depending on Inspection results, remove the

Gussets from FR46, LH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 46

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills AIRFRAME

References

Structural Repair Manual (SRM) 51-40-20

Fig. A-FUAAA

Removal/Installation of the Gussets at

FR46, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

(a) Remove the Gussets from Frame 46, LH side.

Refer to Fig. A-FUAAA

In accordance with SRM 51-40-20

1 Remove:

1 Gusset Item (140) Retain

1 Gusset Item (142) Retain

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 494

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@A300-600

SERVICE BULLETIN

attached with:

4 Screw Item (3) Discard

4 Nut Item (4) Discard

(53) Subtask 536177-831-053-001 - Depending on Inspection results, remove the Frame

Foot from FR46, LH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 46

Manpower Resources

Manhours 16.00

Minimum number of person 2

Subtask elapsed time 8.00

Skills AIRFRAME

References

Structural Repair Manual (SRM) 51-40-20

Fig. A-FKAAA

Replacement of the Frame foot FR46,

LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

(a) Remove the Frame foot from Frame 46, LH side.

Refer to Fig. A-FKAAA

In accordance with SRM 51-40-20

1 Remove:

1 Frame foot Item (110) Discard

1 Stiffener Item (58) Retain

1 Doubler Item (80) Retain

1 Shim Item (81) Retain

1 Splice Item (82) Retain

20 Pin Item (1) Discard

20 Collar Item (2) Discard

2 Rivet Item (19) Discard

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 495

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@A300-600

SERVICE BULLETIN

28 Screw Item (3) Discard

28 Nut Item (4) Discard

And:

4 Screw Item (55) Retain

4 Nut Item (56) Discard

or

4 Nut Item (76) Discard

And:

5 Rivet Item (5) Discard

or

5 Screw Item (93) Discard

5 Nut Item (94) Discard

(54) Subtask 536177-831-054-001 - Depending on Inspection results, install an identical

Frame Foot at FR46, LH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 46

Manpower Resources

Manhours 16.00

Minimum number of person 1

Subtask elapsed time 8.00

Skills AIRFRAME

Material necessary to do the job

Kit 536177A16R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

8 EN6115V3A7 3 SCREW

9 ASNA2529-3 43 NUT

10 EN6115V3A6 11 SCREW

12 ASNA2529-6 3 NUT

14 NAS1726-5E 2 NUT

15 EN6114V5Y8 6 SCREW

16 ASNA2529-5 7 NUT

17 EN6115V3A5 7 SCREW

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 496

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@A300-600

SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

18 EN6115V3A4 2 SCREW

19 ASNA2050DXJ4020 2 RIVET

26 EN6114V6X14 1 SCREW

33 EN6115V3A9 9 SCREW

43 EN6115V3A10 5 SCREW

44 EN6115V3A11 6 SCREW

50 ASNA2001V5-12Y 2 SCREW

52 EN6114V6X17 2 SCREW

54 EN6114V5X12 1 SCREW

56 NSA5057-6 4 NUT

76 NSA5057-7 4 NUT

110 A5711113420095 1 FOOT

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Wash Primer - Structure 04CMA2 As required

Primer Polyurethane Paint -

Corrosion Inhibiting

04EAC2 As required

Polysulfide Sealant -

General Purpose Brushable

06AAA1 As required

Polysulfide Sealant - Fuel

Tank Brushable

06ABA1 As required

Polysulfide Sealant - Fuel

Tank Fillet

06ABB1 As required

References

Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001

Structural Repair Manual (SRM) 51-40-00

51-40-20

51-40-30

51-40-40

Fig. A-FKAAA

Replacement of the Frame foot FR46,

LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Fig. A-FUAAA

Removal/Installation of the Gussets at

FR46, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

(a) Install and drill all the parts.

Refer to Fig. A-FKAAA

In accordance with SRM 51-40-40

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 497

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@A300-600

SERVICE BULLETIN

1 Put all the parts in position as shown on Fig. A-FKAAA.

1 Frame foot A5711113420095 Item 110

1 Stiffener Item (58) Retained at

removal

1 Doubler Item (80) Retained at

removal

1 Shim Item (81) Retained at

removal

1 Splice Item (82) Retained at

removal

NOTE: If necessary, rework the upper and side surfaces of the Frame

foot with a maximum of 0.5 mm (0.020 in.) as shown on Fig.

A-FKAAA Sheet 03.

NOTE: Between parts apply:

Polysulfide Sealant

- Fuel Tank Fillet

06ABB1 As required

2 Drill the holes of the Frame foot H300 to H313, H316 to H331 and H334 to

H341 to the diameter given on Fig. A-FKAAA Sheet 03 and Fig. A-FKAAA

Sheet 04.

3 Drill the holes of the stiffener H314 and H315 to the diameter given on Fig. AFKAAA Sheet 04.

4 Drill the holes of the splice H342 to H354 to the diameter given on Fig. AFKAAA Sheet 05.

(b) Cut-out the Frame foot Item 110 as shown on Fig. A-FKAAA Sheet 03.

Protect the cut-out with:

Wash Primer -

Structure

04CMA2 As required

Primer

Polyurethane Paint

- Corrosion

Inhibiting

04EAC2 As required

(c) Install the fasteners.

Refer to Fig. A-FKAAA

In accordance with SRM 51-40-00, SRM 51-40-20 and SRM 51-40-30

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 498

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@A300-600

SERVICE BULLETIN

Refer to AMM 20-21-12, Page Block 001

1 Install the fasteners of the Frame foot H300 to H313, H316 to H331 and H334

to H341 to H313 and H316 to H341:

Refer to Fig. A-FKAAA Sheet 03 and Fig. A-FKAAA Sheet 04

2 Screw EN6115V3A7 Item 8

8 Screw EN6115V3A6 Item 10

6 Screw EN6114V5Y8 Item 15

9 Screw EN6115V3A9 Item 33

5 Screw EN6115V3A10 Item 43

6 Screw EN6115V3A11 Item 44

2 Screw ASNA2001V5-12Y Item 50

30 Nut ASNA2529-3 Item 9

2 Nut NAS1726-5E Item 14

6 Nut ASNA2529-5 Item 16

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

2 Install the four upper fasteners of the Frame foot:

Refer to Fig. A-FKAAA Sheet 02

4 Bolt Item (55) Retained at

removal

4 Nut NSA5057-6 Item 56

or

4 Nut NSA5057-7 Item 76

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 499

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@A300-600

SERVICE BULLETIN

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

3 Install the fasteners of the stiffener at STGR 37 H314 and H315:

Refer to Fig. A-FKAAA Sheet 04

2 Rivet ASNA2050DXJ4020 Item 19

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

4 Install the fasteners of the splice H342 to H354:

Refer to Fig. A-FKAAA Sheet 05

1 Screw EN6115V3A7 Item 8

3 Screw EN6115V3A6 Item 10

7 Screw EN6115V3A5 Item 17

2 Screw EN6115V3A4 Item 18

13 Nut ASNA2529-3 Item 9

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

5 Do a sealant bead around the parts with:

Polysulfide Sealant

- Fuel Tank Fillet

06ABB1 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 500

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@A300-600

SERVICE BULLETIN

(d) Install the Gussets at Frame 46, LH side.

Refer to Fig. A-FUAAA

In accordance with SRM 51-40-20, SRM 51-40-00, SRM 51-40-30 and SRM

51-40-40

Refer to AMM 20-21-12, Page Block 001

1 Put the gussets in position as shown on Fig. A-FUAAA.

1 Gusset Item (140) Retained at

removal

1 Gusset Item (142) Retained at

removal

NOTE: Between the Frame foot and the aft gusset, the distance must

be 2 times the thickness of the gusset.

NOTE: Between the Frame foot and the FWD gusset, the distance

must be 1.3 times the thickness of the gusset.

2 Drill holes H332 and H333 to the diameter given on Fig. A-FUAAA Sheet 03.

3 Drill holes H355 and H356 to the diameter given on Fig. A-FUAAA Sheet 03.

4 Install:

1 Gusset Item (140) Retained at

removal

1 Gusset Item (142) Retained at

removal

1 Screw EN6114V6X14 Item 26

2 Screw EN6114V6X17 Item 52

1 Screw EN6114V5X12 Item 54

3 Nut ASNA2529-6 Item 12

1 Nut ASNA2529-5 Item 16

(55) Subtask 536177-831-055-001 - Depending on Inspection results, if removed, install

the Fasteners at FR46, LH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 46

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 501

5

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

SERVICE BULLETIN

Manpower Resources

Manhours 6.00

Minimum number of person 2

Subtask elapsed time 3.00

Skills AIRFRAME

Material necessary to do the job

Component COMPA05

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

9 ASNA2529-3 24 NUT

47 EN6114V3X6 16 SCREW

90 ASNA2019-56-25 24 RIVET

91 EN6114V3X5 8 SCREW

92 EN6080D6X-32 16 RIVET

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

NOTE: The components listed above are only necessary if crack is found on a

Frame foot. The quantity of these items are to be ordered as required.

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant - Fuel

Tank Brushable

06ABA1 As required

References

Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001

Structural Repair Manual (SRM) 51-24-00

51-40-00

51-40-20

51-40-30

Fig. A-FVAAA

Removal/Installation of the Fasteners

from FR41 to FR46, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

(a) If removed, install the fasteners at Frame 46, LH side.

Refer to Fig. A-FVAAA

In accordance with SRM 51-40-20, SRM 51-24-00, SRM 51-40-00 and SRM

51-40-30

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 502

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@A300-600

SERVICE BULLETIN

Refer to AMM 20-21-12, Page Block 001

1 Install:

16 Rivet EN6080D6X-32 Item 92

And:

16 Rivet ASNA2019-56-25 Item 90

or

16 Screw EN6114V3X6 Item 47

16 Nut ASNA2529-3 Item 9

And:

8 Rivet ASNA2019-56-25 Item 90

or

8 Screw EN6114V3X5 Item 91

8 Nut ASNA2529-3 Item 9

NOTE: Protect the fasteners with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

(56) Subtask 536177-831-056-001 - Depending on Inspection results, if necessary,

remove the Fasteners from FR46, RH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 46

Manpower Resources

Manhours 4.00

Minimum number of person 2

Subtask elapsed time 2.00

Skills AIRFRAME

References

Structural Repair Manual (SRM) 51-40-20

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 503

5

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@A300-600

SERVICE BULLETIN

References

Fig. A-FVAAA

Removal/Installation of the Fasteners

from FR41 to FR46, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

(a) If necessary, to ease the replacement of the Frame foot, remove fasteners from

Frame 46, RH side.

Refer to Fig. A-FVAAA

In accordance with SRM 51-40-20

1 Remove:

16 Rivet Item (19) Discard

And:

24 Rivet Item (5) Discard

or

24 Bolt Item (3) Discard

24 Nut Item (4) Discard

(57) Subtask 536177-831-057-001 - Depending on Inspection results, remove the

Gussets from FR46, RH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 46

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills AIRFRAME

References

Structural Repair Manual (SRM) 51-40-20

Fig. A-FUAAA

Removal/Installation of the Gussets at

FR46, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

(a) Remove the Gussets from Frame 46, RH side.

Refer to Fig. A-FUAAA

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 504

5

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

SERVICE BULLETIN

In accordance with SRM 51-40-20

1 Remove:

1 Gusset Item (141) Retain

1 Gusset Item (143) Retain

attached with:

4 Screw Item (3) Discard

4 Nut Item (4) Discard

(58) Subtask 536177-831-058-001 - Depending on Inspection results, remove the Frame

Foot from FR46, RH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 46

Manpower Resources

Manhours 16.00

Minimum number of person 2

Subtask elapsed time 8.00

Skills AIRFRAME

References

Structural Repair Manual (SRM) 51-40-20

Fig. A-FKAAA

Replacement of the Frame foot FR46,

LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

(a) Remove the Frame foot from Frame 46, RH side.

Refer to Fig. A-FKAAA

In accordance with SRM 51-40-20

1 Remove:

1 Frame foot Item (111) Discard

1 Stiffener Item (57) Retain

1 Doubler Item (80) Retain

1 Shim Item (81) Retain

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 505

5

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@A300-600

SERVICE BULLETIN

1 Splice Item (83) Retain

20 Pin Item (1) Discard

20 Collar Item (2) Discard

2 Rivet Item (19) Discard

28 Screw Item (3) Discard

28 Nut Item (4) Discard

And:

4 Screw Item (55) Retain

4 Nut Item (56) Discard

or

4 Nut Item (76) Discard

And:

5 Rivet Item (5) Discard

or

5 Screw Item (93) Discard

5 Nut Item (94) Discard

(59) Subtask 536177-831-059-001 - Depending on Inspection results, install an identical

Frame Foot at FR46, RH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 46

Manpower Resources

Manhours 16.00

Minimum number of person 2

Subtask elapsed time 8.00

Skills AIRFRAME

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 506

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

SERVICE BULLETIN

Material necessary to do the job

Kit 536177A34R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

8 EN6115V3A7 3 SCREW

9 ASNA2529-3 43 NUT

10 EN6115V3A6 8 SCREW

12 ASNA2529-6 3 NUT

14 NAS1726-5E 2 NUT

15 EN6114V5Y8 6 SCREW

16 ASNA2529-5 7 NUT

17 EN6115V3A5 7 SCREW

18 EN6115V3A4 2 SCREW

19 ASNA2050DXJ4020 2 RIVET

26 EN6114V6X14 1 SCREW

33 EN6115V3A9 9 SCREW

43 EN6115V3A10 5 SCREW

44 EN6115V3A11 6 SCREW

50 ASNA2001V5-12Y 2 SCREW

52 EN6114V6X17 2 SCREW

54 EN6114V5X12 1 SCREW

56 NSA5057-6 4 NUT

76 NSA5057-7 4 NUT

111 A5711113420195 1 FOOT

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Wash Primer - Structure 04CMA2 As required

Primer Polyurethane Paint -

Corrosion Inhibiting

04EAC2 As required

Polysulfide Sealant -

General Purpose Brushable

06AAA1 As required

Polysulfide Sealant - Fuel

Tank Brushable

06ABA1 As required

Polysulfide Sealant - Fuel

Tank Fillet

06ABB1 As required

References

Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001

Structural Repair Manual (SRM) 51-40-00

51-40-20

51-40-30

51-40-40

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 507

5

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

SERVICE BULLETIN

References

Fig. A-FKAAA

Replacement of the Frame foot FR46,

LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Fig. A-FUAAA

Removal/Installation of the Gussets at

FR46, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

(a) Install and drill all the parts.

Refer to Fig. A-FKAAA

In accordance with SRM 51-40-40

1 Put all the parts in position as shown on Fig. A-FKAAA.

1 Frame foot A5711113420195 Item 111

1 Stiffener Item (57) Retained at

removal

1 Doubler Item (80) Retained at

removal

1 Shim Item (81) Retained at

removal

1 Splice Item (83) Retained at

removal

NOTE: If necessary, rework the upper and side surfaces of the Frame

foot with a maximum of 0.5 mm (0.020 in.) as shown on Fig.

A-FKAAA Sheet 03.

NOTE: Between parts apply:

Polysulfide Sealant

- Fuel Tank Fillet

06ABB1 As required

2 Drill the holes of the Frame foot H300 to H313, H316 to H331 and H334 to

H341 to the diameter given on Fig. A-FKAAA Sheet 03 and Fig. A-FKAAA

Sheet 04.

3 Drill the holes of the stiffener H314 and H315 to the diameter given on Fig. AFKAAA Sheet 04.

4 Drill the holes of the splice H342 to H354 to the diameter given on Fig. AFKAAA Sheet 05.

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 508

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@A300-600

SERVICE BULLETIN

(b) Cut-out the Frame foot Item 110 as shown on Fig. A-FKAAA Sheet 03.

Protect the cut-out with:

Wash Primer -

Structure

04CMA2 As required

Primer

Polyurethane Paint

- Corrosion

Inhibiting

04EAC2 As required

(c) Install the fasteners.

Refer to Fig. A-FKAAA

In accordance with SRM 51-40-00, SRM 51-40-20 and SRM 51-40-30

Refer to AMM 20-21-12, Page Block 001

1 Install the fasteners of the Frame foot H300 to H313, H316 to H331 and H334

to H341 to H313 and H316 to H341:

Refer to Fig. A-FKAAA Sheet 03 and Fig. A-FKAAA Sheet 04

2 Screw EN6115V3A7 Item 8

5 Screw EN6115V3A6 Item 10

6 Screw EN6114V5Y8 Item 15

9 Screw EN6115V3A9 Item 33

5 Screw EN6115V3A10 Item 43

6 Screw EN6115V3A11 Item 44

2 Screw ASNA2001V5-12Y Item 50

30 Nut ASNA2529-3 Item 9

2 Nut NAS1726-5E Item 14

6 Nut ASNA2529-5 Item 16

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 509

5

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@A300-600

SERVICE BULLETIN

2 Install the four upper fasteners of the Frame foot:

Refer to Fig. A-FKAAA Sheet 02

4 Bolt Item (55) Retained at

removal

4 Nut NSA5057-6 Item 56

or

4 Nut NSA5057-7 Item 76

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

3 Install the fasteners of the stiffener at STGR 37 H314 and H315:

Refer to Fig. A-FKAAA Sheet 04

2 Rivet ASNA2050DXJ4020 Item 19

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

4 Install the fasteners of the splice H342 to H354:

Refer to Fig. A-FKAAA Sheet 05

1 Screw EN6115V3A7 Item 8

3 Screw EN6115V3A6 Item 10

7 Screw EN6115V3A5 Item 17

2 Screw EN6115V3A4 Item 18

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 510

5

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@A300-600

SERVICE BULLETIN

13 Nut ASNA2529-3 Item 9

NOTE: Wet install the fasteners with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

NOTE: Protect the fasteners head and nuts with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

5 Do a sealant bead around the parts with:

Polysulfide Sealant

- Fuel Tank Fillet

06ABB1 As required

(d) Install the Gussets at Frame 46, LH side.

Refer to Fig. A-FUAAA

In accordance with SRM 51-40-20, SRM 51-40-00, SRM 51-40-30 and SRM

51-40-40

Refer to AMM 20-21-12, Page Block 001

1 Put the gussets in position as shown on Fig. A-FUAAA.

1 Gusset Item (141) Retained at

removal

1 Gusset Item (143) Retained at

removal

NOTE: Between the Frame foot and the aft gusset, the distance must

be 2 times the thickness of the gusset.

NOTE: Between the Frame foot and the FWD gusset, the distance

must be 1.3 times the thickness of the gusset.

2 Drill holes H332 and H333 to the diameter given on Fig. A-FUAAA Sheet 03.

3 Drill holes H355 and H356 to the diameter given on Fig. A-FUAAA Sheet 03.

4 Install:

1 Gusset Item (141) Retained at

removal

1 Gusset Item (143) Retained at

removal

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 511

5

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@A300-600

SERVICE BULLETIN

1 Screw EN6114V6X14 Item 26

2 Screw EN6114V6X17 Item 52

1 Screw EN6114V5X12 Item 54

3 Nut ASNA2529-6 Item 12

1 Nut ASNA2529-5 Item 16

(60) Subtask 536177-831-060-001 - Depending on Inspection results, install the

Fasteners at FR46, RH side

Work Zones and Access Panels

Zone Access/Work location

140 Work location Frame 46

Manpower Resources

Manhours 6.00

Minimum number of person 2

Subtask elapsed time 3.00

Skills AIRFRAME

Material necessary to do the job

Component COMPA05

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

9 ASNA2529-3 24 NUT

47 EN6114V3X6 16 SCREW

90 ASNA2019-56-25 24 RIVET

91 EN6114V3X5 8 SCREW

92 EN6080D6X-32 16 RIVET

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

NOTE: The components listed above are only necessary if crack is found on a

Frame foot. The quantity of these items are to be ordered as required.

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant - Fuel

Tank Brushable

06ABA1 As required

References

Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 512

5

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@A300-600

SERVICE BULLETIN

References

Structural Repair Manual (SRM) 51-24-00

51-40-00

51-40-20

51-40-30

Fig. A-FVAAA

Removal/Installation of the Fasteners

from FR41 to FR46, LH and RH Sides

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

(a) If removed, install the fasteners at Frame 46, RH side.

Refer to Fig. A-FVAAA

In accordance with SRM 51-40-20, SRM 51-24-00, SRM 51-40-00 and SRM

51-40-30

Refer to AMM 20-21-12, Page Block 001

1 Install:

16 Rivet EN6080D6X-32 Item 92

And:

16 Rivet ASNA2019-56-25 Item 90

or

16 Screw EN6114V3X6 Item 47

16 Nut ASNA2529-3 Item 9

And:

8 Rivet ASNA2019-56-25 Item 90

or

8 Screw EN6114V3X5 Item 91

8 Nut ASNA2529-3 Item 9

NOTE: Protect the fasteners with:

Polysulfide Sealant

- Fuel Tank

Brushable

06ABA1 As required

**CONF 004

None

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 513

5

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@A300-600

SERVICE BULLETIN

**CONF ALL

D. TEST

**CONF 001

(1) Subtask 536177-700-003-001 - Testing

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 28-11-29, Page Block 401

This Service Bulletin requires the accomplishment of the following Tests which are given

in subtasks included in the topic Close-up. The manhours for the tests are included in

the referenced Service Bulletin subtasks.

- Remove the safety clip(s) and/or tag(s) and close/unlock the circuit breaker(s) as

specified after the installation of the center tank manhole cover (147AZ and 148AZ),

refer to AMM 28-11-29, Page Block 401.

- Do the test procedure as specified after the installation of the center tank manhole

cover (147AZ and 148AZ), refer to AMM 28-11-29, Page Block 401.

**CONF 002

(1) Subtask 536177-700-003-001 - Testing

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 28-11-29, Page Block 401

This Service Bulletin requires the accomplishment of the following Tests which are given

in subtasks included in the topic Close-up. The manhours for the tests are included in

the referenced Service Bulletin subtasks.

- Remove the safety clip(s) and/or tag(s) and close/unlock the circuit breaker(s) as

specified after the installation of the center tank manhole cover (147AZ and 148AZ),

refer to AMM 28-11-29, Page Block 401.

- Do the test procedure as specified after the installation of the center tank manhole

cover (147AZ and 148AZ), refer to AMM 28-11-29, Page Block 401.

**CONF 003

(1) Subtask 536177-700-003-001 - Testing

Manpower Resources

Skills NON SPECIFIC

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 514

5

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@A300-600

SERVICE BULLETIN

References

Aircraft Maintenance Manual (AMM) 28-11-29, Page Block 401

This Service Bulletin requires the accomplishment of the following Tests which are given

in subtasks included in the topic Close-up. The manhours for the tests are included in

the referenced Service Bulletin subtasks.

- Remove the safety clip(s) and/or tag(s) and close/unlock the circuit breaker(s) as

specified after the installation of the center tank manhole cover (147AZ and 148AZ),

refer to AMM 28-11-29, Page Block 401.

- Do the test procedure as specified after the installation of the center tank manhole

cover (147AZ and 148AZ), refer to AMM 28-11-29, Page Block 401.

**CONF 004

None

**CONF ALL

E. CLOSE-UP

**CONF 001

(1) Subtask 536177-942-003-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 28-11-00, Page Block 501

28-11-29, Page Block 401

28-13-21, Page Block 401

WARNING: MAKE CERTAIN THAT FIRE FIGHTING EQUIPMENT IS AVAILABLE

AND ADEQUATE.

OBEY THE FUEL SERVICING SAFETY INSTRUCTIONS.

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) Close the access door 147BZ.

(c) Close the access doors 147AZ and 148AZ, refer to AMM 28-11-29, Page Block

401.

(d) Remove the access platform(s).

(e) Install the vapor seals, refer to AMM 28-13-21, Page Block 401.

(f) Refuel the center tank, refer to AMM 28-11-00, Page Block 501.

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 515

5

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@A300-600

SERVICE BULLETIN

(g) Put the aircraft back to its initial configuration.

**CONF 002

(1) Subtask 536177-942-003-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 28-11-00, Page Block 501

28-11-29, Page Block 401

28-13-21, Page Block 401

WARNING: MAKE CERTAIN THAT FIRE FIGHTING EQUIPMENT IS AVAILABLE

AND ADEQUATE.

OBEY THE FUEL SERVICING SAFETY INSTRUCTIONS.

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) Close the access door 147BZ.

(c) Close the access doors 147AZ and 148AZ, refer to AMM 28-11-29, Page Block

401.

(d) Remove the access platform(s).

(e) Install the vapor seals, refer to AMM 28-13-21, Page Block 401.

(f) Refuel the center tank, refer to AMM 28-11-00, Page Block 501.

(g) Put the aircraft back to its initial configuration.

**CONF 003

(1) Subtask 536177-942-003-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 28-11-00, Page Block 501

28-11-29, Page Block 401

28-13-21, Page Block 401

WARNING: MAKE CERTAIN THAT FIRE FIGHTING EQUIPMENT IS AVAILABLE

AND ADEQUATE.

OBEY THE FUEL SERVICING SAFETY INSTRUCTIONS.

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 516

5

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@A300-600

SERVICE BULLETIN

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) Close the access door 147BZ.

(c) Close the access doors 147AZ and 148AZ, refer to AMM 28-11-29, Page Block

401.

(d) Remove the access platform(s).

(e) Install the vapor seals, refer to AMM 28-13-21, Page Block 401.

(f) Refuel the center tank, refer to AMM 28-11-00, Page Block 501.

(g) Put the aircraft back to its initial configuration.

**CONF 004

None

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 517

5

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@A300-600

SERVICE BULLETIN

This Page Intentionally Left Blank

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 518

5

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@A300-600

SERVICE BULLETIN

Task 536177-839-801-001 - Contact and Report to AIRBUS

**CONF ALL

Task Associated Data

**CONF 001

None

**CONF 002

None

**CONF 003

None

**CONF 004

Manpower

TOTAL MANHOURS 0.50

ELAPSED TIME (HOURS) 0.50

**CONF ALL

A. GENERAL

**CONF 001

None

**CONF 002

None

**CONF 003

None

**CONF 004

None

**CONF ALL

B. PREPARATION

**CONF 001

None

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 519

5

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@A300-600

SERVICE BULLETIN

**CONF 002

None

**CONF 003

None

**CONF 004

None

**CONF ALL

C. PROCEDURE

**CONF 001

None

**CONF 002

None

**CONF 003

None

**CONF 004

(1) Subtask 536177-839-003-001 - Contact and Report to AIRBUS

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills NON SPECIFIC

NOTE: No physical work is required on aircraft.

(a) At threshold given in the PLANNING INFORMATION Paragraph E.(2):

1 Verify that the Frame is covered by RDAS.

2 Contact and report to AIRBUS within 6 months from Service Bulletin issuance

date.

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 520

5

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@A300-600

SERVICE BULLETIN

**CONF ALL

D. TEST

**CONF 001

None

**CONF 002

None

**CONF 003

None

**CONF 004

None

**CONF ALL

E. CLOSE-UP

**CONF 001

None

**CONF 002

None

**CONF 003

None

**CONF 004

None

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 521

5

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@A300-600

SERVICE BULLETIN

**CONF ALL

B C

F G

D E

K L

H J

M N

A

Z140

FR41

FR42

FR43

FR44

FR45

FR46

A

B C

D E

F G

H J

K L

M N

D_SB_536177_5_BAAA_01_02

Figure A-FBAAA - Sheet 01

Inspection areas

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 522

5

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@A300-600

SERVICE BULLETIN

**CONF ALL

STGR35

LH SHOWN

RH SYMMETRICAL

VIEW LOOKING AFTERWARD

FR41

B

STGR35

LH SHOWN

RH SYMMETRICAL

VIEW LOOKING AFTERWARD

FR41

CRACK

C

NOTE:

AREA TO BE INSPECTED

AREA 2

Q

CRACK

AREA 1

P

D_SB_536177_5_BAAA_02_00

Figure A-FBAAA - Sheet 02

Inspection areas

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 523

5

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@A300-600

SERVICE BULLETIN

**CONF ALL

CRACK

STGR36

STGR37

LH SHOWN

RH SYMMETRICAL

VIEW LOOKING AFTERWARD

FR42

E

NOTE:

AREA TO BE INSPECTED

CRACK

STGR36

STGR37

LH SHOWN

RH SYMMETRICAL

VIEW LOOKING AFTERWARD

FR42

D

AREA 2

AREA 1

Q

P

D_SB_536177_5_BAAA_03_00

Figure A-FBAAA - Sheet 03

Inspection areas

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 524

5

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@A300-600

SERVICE BULLETIN

**CONF ALL

LH SHOWN

RH SYMMETRICAL

VIEW LOOKING AFTERWARD

FR43

LH SHOWN

RH SYMMETRICAL

VIEW LOOKING AFTERWARD

FR43

STGR36

CRACK

STGR36

G

NOTE:

AREA TO BE INSPECTED

F

CRACK

P

Q

AREA 2

AREA 1

D_SB_536177_5_BAAA_04_00

Figure A-FBAAA - Sheet 04

Inspection areas

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 525

5

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@A300-600

SERVICE BULLETIN

**CONF ALL

STGR36

STGR37

CRACK

LH SHOWN

RH SYMMETRICAL

VIEW LOOKING AFTERWARD

FR44

H

STGR36

STGR37

CRACK

LH SHOWN

RH SYMMETRICAL

VIEW LOOKING AFTERWARD

FR44

J

NOTE:

AREA TO BE INSPECTED

AREA 1

Q

AREA 2

P

D_SB_536177_5_BAAA_05_00

Figure A-FBAAA - Sheet 05

Inspection areas

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 526

5

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@A300-600

SERVICE BULLETIN

**CONF ALL

CRACK

STGR37

LH SHOWN

RH SYMMETRICAL

VIEW LOOKING AFTERWARD

FR45

K

CRACK

STGR37

LH SHOWN

RH SYMMETRICAL

VIEW LOOKING AFTERWARD

FR45

L

NOTE:

AREA TO BE INSPECTED

P

AREA 2

AREA 1

Q

D_SB_536177_5_BAAA_06_00

Figure A-FBAAA - Sheet 06

Inspection areas

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 527

5

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@A300-600

SERVICE BULLETIN

**CONF ALL

STGR37

CRACK

LH SHOWN

RH SYMMETRICAL

VIEW LOOKING AFTERWARD

FR46

STGR37

CRACK

LH SHOWN

RH SYMMETRICAL

VIEW LOOKING AFTERWARD

FR46

N

M

NOTE:

AREA TO BE INSPECTED

AREA 1

Q

P

AREA 2

D_SB_536177_5_BAAA_07_00

Figure A-FBAAA - Sheet 07

Inspection areas

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 528

5

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@A300-600

SERVICE BULLETIN

**CONF ALL

BASE FITTING

AREA 1

FWD P

FWD Q

NOTE:

AREA TO BE INSPECTED

TYPICAL

TYPICAL

FOR REPAIRED FRAMES, THE NEW CRACKS ARE

DETECTABLE IN THE FRAME FOOT FLANGE FIRST

BASE FITTING

AREA 2

D_SB_536177_5_BAAA_08_01

Figure A-FBAAA - Sheet 08

Inspection areas

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 529

5

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@A300-600

SERVICE BULLETIN

**CONF 003

FR40

A

B

FR41

FR47

FR41

B

Z140

A

C

D

F

C

D

F

D_SB_536177_5_CAAA_01_00

Figure A-FCAAA - Sheet 01

Replacement of the Frame foot FR41, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 530

5

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@A300-600

SERVICE BULLETIN

**CONF 003

RH SYMMETRICAL

VIEW LOOKING AFT

LH SHOWN

A A

F

W

D

C

(55)

01 WET INSTALL THE FASTENERS WITH MAT No 06AAA1 EXCEPT FOR HOLES H24 AND H25

PROTECT THE FASTENERS HEAD AND NUTS WITH MAT No 06ABA1

DO SEALANT BEAD AROUND PARTS WITH MAT No 06ABB1

APPLY MAT No 06ABB1 BETWEEN PARTS

01

(56) 56

NOTE:

A A

FR41

INBOARD

OUTBOARD

D_SB_536177_5_CAAA_02_01

Figure A-FCAAA - Sheet 02

Replacement of the Frame foot FR41, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 531

5

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@A300-600

SERVICE BULLETIN

**CONF 003

D

RH SYMMETRICAL

VIEW LOOKING AFT

LH SHOWN

FR41

LH

RH

(100)

(101)

H18

H14

H13

H12

H19

H10 H11

H23

H22

H21

H20

H15

H16

H17

H8

H6

H4

H2 H1

H3

H5

H7

H9

STGR35

E

01 WET INSTALL THE FASTENERS WITH MAT. No 06AAA1 EXCEPT FOR HOLES H24 AND H25

PROTECT THE FASTENERS HEAD AND NUTS WITH MAT. No 06ABA1

DO SEALANT BEAD AROUND PARTS WITH MAT No 06ABB1 APPLY MAT. No 06ABB1 BETWEEN PARTS

02 PROTECT THE CUTÜOUT AREA WITH MAT No 04CMA2 AND MAT. No 04EAC2

NOTE:

FASTENERS NOT AFFECTED

HOLE

SYMBOL ITEM P/N DESCRIPTION HOLE DIAMETER

MIN MAX

ASNA2529Ü3

(1)

(2) NUT

SCREW 5.552 mm

(0.218 in)

5.512 mm

(0.217 in)

ASNA2529Ü3

(3)

(4) NUT

SCREW

ASNA2529Ü3

(3)

(4) NUT

SCREW

N

N

F

8

9

10

9

10

9

EN6115V3A7

EN6115V3A6

EN6115V3A6

5.552 mm

(0.218 in)

5.512 mm

(0.217 in)

5.552 mm

(0.218 in)

5.512 mm

(0.217 in)

HEAD ON THE VISIBLE SIDE N

HEAD ON THE HIDDEN SIDE F

100

101

02 CUTÜOUT

01

INBOARD

OUTBOARD

04

04

04

B

B

C

C

04 REWORK THE SURFACES WITH MAXIMUM OF THE 0.5 mm (0.020 in)

DURING THE INSTALLATION OF THE NEW FRAME FOOT

C

C

D_SB_536177_5_CAAA_03_01

Figure A-FCAAA - Sheet 03

Replacement of the Frame foot FR41, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 532

5

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@A300-600

SERVICE BULLETIN

**CONF 003

FWD

STGR35

(57)

(58)

RH

LH

B B

FR41

H46

H45

01 WET INSTALL THE FASTENERS WITH MAT. No 06AAA1 EXCEPT FOR HOLES H24 AND H25

PROTECT THE FASTENERS HEAD AND NUTS WITH MAT. No 06ABA1

DO SEALANT BEAD AROUND PARTS WITH MAT. No 06ABB1 APPLY MAT. No 06ABB1 BETWEEN PARTS

03 USE EXISTING HOLES IN STRINGERS FOR THE INSTALLATION OF STIFFENERS

HOLE

SYMBOL ITEM P/N DESCRIPTION

HOLE DIAMETER

MIN MAX

ASNA2529Ü6

(3)

(4) NUT

SCREW 9.925 mm

(0.391 in)

9.886 mm

(0.389 in)

NAS1726Ü5E

(3)

(4) NUT

SCREW

ASNA2529Ü5

(3)

(4) NUT

SCREW

N

N

N

26

12

13

14

15

16

EN6114V6X14

ASNA2001V5Ü8Y

EN6114V5Y8

8.732 mm

(0.344 in)

8.692 mm

(0.342 in)

HEAD ON THE VISIBLE SIDE N

NOTE:

(5) RIVET N 19 ASNA2050DXJ4020 4.170 mm

(0.164 in)

4.060 mm

(0.160 in)

8.732 mm

(0.344 in)

8.692 mm

(0.342 in)

E

03

01

01

(100)

(101)

LH

RH

100

101

H29 H28

H27 H26

H25 H24

H31 H30

05 05

FRAME FOOT

C C

05 SPOTFACES TO BE REALIZED DURING INSTALLATION AFTER DRILLING OF PARTS TO DIAMETER 27 mm

(1.063 in) FOR OLD FASTENERS DIAMETER 9.52 mm (0.375 in) AND TO DIAMETER 29 mm (1.142 in)

 FOR OLD FASTENERS DIAMETER 11.1 mm (0.437 in)

TYPICAL SECTION

ELECTRICAL BONDING

D_SB_536177_5_CAAA_04_01

Figure A-FCAAA - Sheet 04

Replacement of the Frame foot FR41, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 533

5

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@A300-600

SERVICE BULLETIN

**CONF 003

FWD

(60)

(59)

LH

RH

FR41

STGR37

STGR36

H39

H38

H37

H36

H35

H34

H33

H32

H44

H43

H42

H41

FR41

RH SYMMETRICAL

VIEW LOOKING AFT

LH SHOWN FR41

(59)

(60)

(61)

RH

LH C C

01 WET INSTALL THE FASTENERS WITH MAT. No 06AAA1 EXCEPT FOR HOLES H24 AND H25

PROTECT THE FASTENERS HEAD AND NUTS WITH MAT. No 06ABA1

DO SEALANT BEAD AROUND PARTS WITH MAT. No 06ABB1 APPLY MAT. No 06ABB1 BETWEEN PARTS

NOTE:

HOLE

SYMBOL ITEM P/N DESCRIPTION

HOLE DIAMETER

MIN MAX

ASNA2529Ü3

(3)

(4) NUT

SCREW 5.552 mm

(0.218 in)

5.512 mm

(0.217 in)

ASNA2529Ü3

(3)

(4) NUT

SCREW

ASNA2529Ü3

(3)

(4) NUT

SCREW

N

N

N

17

9

8

9

18

9

EN6115V3A5

EN6115V3A7

EN6115V3A4

5.552 mm

(0.218 in)

5.512 mm

(0.217 in)

5.552 mm

(0.218 in)

5.512 mm

(0.217 in)

HEAD ON THE VISIBLE SIDE N

G

H40

FASTENERS NOT AFFECTED

C

C

F

G

01

01

H14

INBOARD

OUTBOARD

D_SB_536177_5_CAAA_05_00

Figure A-FCAAA - Sheet 05

Replacement of the Frame foot FR41, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 534

5

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SERVICE BULLETIN

**CONF 002

FR40

A

B

FR41

FR47

FR41

B

Z140

A

C

D

F

C

D

F

D_SB_536177_5_CAAB_01_00

Figure A-FCAAB - Sheet 01

Replacement of the Frame foot FR41, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 535

5

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@A300-600

SERVICE BULLETIN

**CONF 002

RH SYMMETRICAL

VIEW LOOKING AFT

LH SHOWN

A A

F

W

D

C

(55)

01 WET INSTALL THE FASTENERS WITH MAT No 06AAA1 EXCEPT FOR HOLES H24 AND H25

PROTECT THE FASTENERS HEAD AND NUTS WITH MAT No 06ABA1

DO SEALANT BEAD AROUND PARTS WITH MAT No 06ABB1

APPLY MAT No 06ABB1 BETWEEN PARTS

01

(56) 56

NOTE:

A A

FR41

INBOARD

OUTBOARD

D_SB_536177_5_CAAB_02_01

Figure A-FCAAB - Sheet 02

Replacement of the Frame foot FR41, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 536

5

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@A300-600

SERVICE BULLETIN

**CONF 002

D

RH SYMMETRICAL

VIEW LOOKING AFT

LH SHOWN

FR41

LH

RH

(100)

(101)

H18

H14

H13

H12

H19

H10 H11

H23

H22

H21

H20

H15

H16

H17

H8

H6

H4

H2 H1

H3

H5

H7

H9

STGR35

E

01 WET INSTALL THE FASTENERS WITH MAT. No 06AAA1 EXCEPT FOR HOLES H24 AND H25

PROTECT THE FASTENERS HEAD AND NUTS WITH MAT. No 06ABA1

DO SEALANT BEAD AROUND PARTS WITH MAT No 06ABB1 APPLY MAT. No 06ABB1 BETWEEN PARTS

02 PROTECT THE CUTÜOUT AREA WITH MAT No 04CMA2 AND MAT. No 04EAC2

NOTE:

FASTENERS NOT AFFECTED

HOLE

SYMBOL ITEM P/N DESCRIPTION HOLE DIAMETER

MIN MAX

HEAD ON THE VISIBLE SIDE N

HEAD ON THE HIDDEN SIDE F

100

101

02 CUTÜOUT

01

INBOARD

OUTBOARD

04

04

04

B

B

C

C

04 REWORK THE SURFACES WITH MAXIMUM OF THE 0.5 mm (0.020 in)

DURING THE INSTALLATION OF THE NEW FRAME FOOT

C

C

ASNA2529Ü3

(1)

(2) NUT

SCREW 5.552 mm

(0.218 in)

5.512 mm

(0.217 in)

ASNA2529Ü3

(1)

(2) NUT

SCREW

ASNA2529Ü3

(1)

(2) NUT

SCREW

N

N

F

8

9

10

9

10

9

EN6115V3A7

EN6115V3A6

EN6115V3A6

5.552 mm

(0.218 in)

5.512 mm

(0.217 in)

5.552 mm

(0.218 in)

5.512 mm

(0.217 in)

D_SB_536177_5_CAAB_03_01

Figure A-FCAAB - Sheet 03

Replacement of the Frame foot FR41, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 537

5

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

SERVICE BULLETIN

**CONF 002

FWD

STGR35

(57)

(58)

RH

LH

B B

FR41

H46

H45

01 WET INSTALL THE FASTENERS WITH MAT. No 06AAA1 EXCEPT FOR HOLES H24 AND H25

PROTECT THE FASTENERS HEAD AND NUTS WITH MAT. No 06ABA1

DO SEALANT BEAD AROUND PARTS WITH MAT. No 06ABB1 APPLY MAT. No 06ABB1 BETWEEN PARTS

03 USE EXISTING HOLES IN STRINGERS FOR THE INSTALLATION OF STIFFENERS

HOLE

SYMBOL ITEM P/N DESCRIPTION

HOLE DIAMETER

MIN MAX

HEAD ON THE VISIBLE SIDE N

NOTE:

E

03

01

01

(100)

(101)

LH

RH

100

101

H29 H28

H27 H26

H25 H24

H31 H30

05 05

FRAME FOOT

C C

05 SPOTFACES TO BE REALIZED DURING INSTALLATION AFTER DRILLING OF PARTS TO DIAMETER 27 mm

(1.063 in) FOR OLD FASTENERS DIAMETER 9.52 mm (0.375 in) AND TO DIAMETER 29 mm (1.142 in)

 FOR OLD FASTENERS DIAMETER 11.1 mm (0.437 in)

TYPICAL SECTION

ASNA2529Ü6

(1)

(2) NUT

SCREW 10.321 mm

(0.406 in)

10.282 mm

(0.405 in)

NAS1726Ü5E

(3)

(4) NUT

SCREW

ASNA2529Ü5

(1)

(2) NUT

SCREW

N

N

N

11

12

13

14

15

16

EN6114V6Y14

ASNA2001V5Ü8Y

EN6114V5Y8

8.732 mm

(0.344 in)

8.692 mm

(0.342 in)

(5) RIVET N 19 ASNA2050DXJ4020 4.170 mm

(0.164 in)

4.060 mm

(0.160 in)

8.732 mm

(0.344 in)

8.692 mm

(0.342 in)

ELECTRICAL BONDING

D_SB_536177_5_CAAB_04_01

Figure A-FCAAB - Sheet 04

Replacement of the Frame foot FR41, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 538

5

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

SERVICE BULLETIN

**CONF 002

FWD

(60)

(59)

LH

RH

FR41

STGR37

STGR36

H39

H38

H37

H36

H35

H34

H33

H32

H44

H43

H42

H41

FR41

RH SYMMETRICAL

VIEW LOOKING AFT

LH SHOWN

FR41

(59)

(60)

(61)

RH

LH

C C

01 WET INSTALL THE FASTENERS WITH MAT. No 06AAA1 EXCEPT FOR HOLES H24 AND H25

PROTECT THE FASTENERS HEAD AND NUTS WITH MAT. No 06ABA1

DO SEALANT BEAD AROUND PARTS WITH MAT. No 06ABB1 APPLY MAT. No 06ABB1 BETWEEN PARTS

NOTE:

HOLE

SYMBOL ITEM P/N DESCRIPTION

HOLE DIAMETER

MIN MAX

ASNA2529Ü3

(1)

(2) NUT

SCREW 5.552 mm

(0.218 in)

5.512 mm

(0.217 in)

ASNA2529Ü3

(1)

(2) NUT

SCREW

ASNA2529Ü3

(1)

(2) NUT

SCREW

N

N

N

8

9

17

9

18

9

EN6115V3A7

EN6115V3A5

EN6115V3A4

5.552 mm

(0.218 in)

5.512 mm

(0.217 in)

5.552 mm

(0.218 in)

5.512 mm

(0.217 in)

HEAD ON THE VISIBLE SIDE N

G

H40

FASTENERS NOT AFFECTED

C

C

F

G

01

01

H14

INBOARD

OUTBOARD

D_SB_536177_5_CAAB_05_00

Figure A-FCAAB - Sheet 05

Replacement of the Frame foot FR41, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 539

5

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

SERVICE BULLETIN

**CONF 001

FR40

A

B

FR41

FR47

FR41

B

Z140

A

C

F

C

F

D

D

D_SB_536177_5_CAAC_01_00

Figure A-FCAAC - Sheet 01

Replacement of the Frame foot FR41, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 540

5

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

SERVICE BULLETIN

**CONF 001

RH SYMMETRICAL

VIEW LOOKING AFT

LH SHOWN

F

W

D

C

(55)

01 WET INSTALL THE FASTENERS WITH MAT No 06AAA1 EXCEPT FOR HOLES H24 AND H25

PROTECT THE FASTENERS HEAD AND NUTS WITH MAT No 06ABA1

DO SEALANT BEAD AROUND PARTS WITH MAT No 06ABB1

APPLY MAT No 06ABB1 BETWEEN PARTS

01

(56) 56

NOTE:

A A

FR41

INBOARD

OUTBOARD

A A

D_SB_536177_5_CAAC_02_01

Figure A-FCAAC - Sheet 02

Replacement of the Frame foot FR41, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 541

5

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

SERVICE BULLETIN

**CONF 001

D

RH SYMMETRICAL

VIEW LOOKING AFT

LH SHOWN

FR41

LH

RH

(100)

(101)

H18

H14

H13

H12

H19

H10 H11

H23

H22

H21

H20

H15

H16

H17

H8

H6

H4

H2 H1

H3

H5

H7

H9

STGR35

E

01 WET INSTALL THE FASTENERS WITH MAT. No 06AAA1 EXCEPT FOR HOLES H24 AND H25

PROTECT THE FASTENERS HEAD AND NUTS WITH MAT. No 06ABA1

DO SEALANT BEAD AROUND PARTS WITH MAT No 06ABB1 APPLY MAT. No 06ABB1 BETWEEN PARTS

NOTE:

FASTENERS NOT AFFECTED

100

101

01

INBOARD

OUTBOARD

03

03

03

B

B

C

C

03 REWORK THE SURFACES WITH MAXIMUM OF THE 0.5 mm (0.020 in)

DURING THE INSTALLATION OF THE NEW FRAME FOOT

C

C

D_SB_536177_5_CAAC_03_01

Figure A-FCAAC - Sheet 03

Replacement of the Frame foot FR41, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 542

5

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

SERVICE BULLETIN

**CONF 001

5.113 mm

(0.201 in)

5.113 mm

(0.201 in)

5.152 mm

(0.203 in)

5.152 mm

(0.203 in)

9

23

9

24

NUT

SCREW

NUT

SCREW

ASNA2529Ü3

EN6115V3X5

ASNA2529Ü3

EN6115V3X7

5.113 mm

(0.201 in)

5.152 mm

9 (0.203 in)

25

NUT

SCREW

ASNA2529Ü3

EN6115V3X6

5.113 mm

(0.201 in)

5.152 mm

9 (0.203 in)

23

NUT

SCREW

ASNA2529Ü3

EN6115V3X5

PART NUMBER DESCRIPTION

HOLE DIAMETER

MIN MAX

(7)

(6)

(4)

(3)

N

N (4)

(3)

(5)

HOLE

SYMBOL ITEM

N

HEAD ON THE VISIBLE SIDE N

HEAD ON THE HIDDEN SIDE F

NOTE:

OR

5.113 mm

(0.201 in)

5.152 mm

9 (0.203 in)

24

NUT

SCREW

ASNA2529Ü3

EN6115V3X7

5.113 mm

(0.201 in)

5.152 mm

9 (0.203 in)

24

NUT

SCREW

ASNA2529Ü3

EN6115V3X7

(7)

(6)

(5)

N OR

5.113 mm

(0.201 in)

5.152 mm

9 (0.203 in)

25

NUT

SCREW

ASNA2529Ü3

EN6115V3X6

5.113 mm

(0.201 in)

5.152 mm

9 (0.203 in)

25

NUT

SCREW

ASNA2529Ü3

EN6115V3X6

(7)

(6)

(5)

N OR

5.113 mm

(0.201 in)

5.152 mm

9 (0.203 in)

25

NUT

SCREW

ASNA2529Ü3

EN6115V3X6

F (4)

(3)

D_SB_536177_5_CAAC_04_00

Figure A-FCAAC - Sheet 04

Replacement of the Frame foot FR41, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 543

5

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

SERVICE BULLETIN

**CONF 001

FWD

STGR35

(57)

(58)

RH

LH

B B

FR41

H46

H45

01 WET INSTALL THE FASTENERS WITH MAT. No 06AAA1 EXCEPT FOR HOLES H24 AND H25

PROTECT THE FASTENERS HEAD AND NUTS WITH MAT. No 06ABA1

DO SEALANT BEAD AROUND PARTS WITH MAT. No 06ABB1 APPLY MAT. No 06ABB1 BETWEEN PARTS

02 USE EXISTING HOLES IN STRINGERS FOR THE INSTALLATION OF STIFFENERS

HEAD ON THE VISIBLE SIDE N

NOTE:

E

02

01

01

(100)

(101)

LH

RH

100

101

H29 H28

H27 H26

H25 H24

H31 H30

04 04

FRAME FOOT

C C

04 SPOTFACES TO BE REALIZED DURING INSTALLATION AFTER DRILLING OF PARTS TO DIAMETER 27 mm

(1.063 in) FOR OLD FASTENERS DIAMETER 9.52 mm (0.375 in) AND TO DIAMETER 29 mm (1.142 in)

 FOR OLD FASTENERS DIAMETER 11.1 mm (0.437 in)

TYPICAL SECTION

9.886 mm

(0.389 in)

 9.925 mm

12 (0.391 in)

26

NUT

SCREW

ASNA2529Ü6

EN6114V6X14

8.296 mm

(0.327 in)

8.335 mm

14 (0.328 in)

27

NUT

SCREW

NAS1726Ü5E

ASNA2001V5Ü8X

PART NUMBER DESCRIPTION

HOLE DIAMETER

MIN MAX

(4)

(3)

N

N (4)

(3)

HOLE

SYMBOL ITEM

8.296 mm

(0.327 in)

8.335 mm

16 (0.328 in)

28

NUT

SCREW

ASNA2529Ü5

EN6114V5X8

N (4)

(3)

4.060 mm

(0.160 in)

4.170 mm

(0.164 in) (19) 19 ASNA2050DXJ4020 RIVET N

ELECTRICAL BONDING

D_SB_536177_5_CAAC_05_01

Figure A-FCAAC - Sheet 05

Replacement of the Frame foot FR41, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 544

5

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

SERVICE BULLETIN

**CONF 001

FWD

(60)

(59)

LH

RH

FR41

STGR37

STGR36

H39

H38

H37

H36

H35

H34

H33

H32

H44

H43

H42

H41

FR41

RH SYMMETRICAL

VIEW LOOKING AFT

LH SHOWN

G

H40

G

F 01

01

FASTENERS NOT AFFECTED

NOTE:

5.113 mm

(0.201 in)

5.152 mm

9 (0.203 in)

23

NUT

SCREW

ASNA2529Ü3

EN6115V3X5

5.113 mm

(0.201 in)

5.152 mm

9 (0.203 in)

24

NUT

SCREW

ASNA2529Ü3

EN6115V3X7

PART NUMBER DESCRIPTION

HOLE DIAMETER

MIN MAX

(4)

(3)

N

N (4)

(3)

HOLE

SYMBOL ITEM

5.113 mm

(0.201 in)

5.152 mm

9 (0.203 in)

29

NUT

SCREW

ASNA2529Ü3

EN6115V3X4

N (4)

(3)

01 WET INSTALL THE FASTENERS WITH MAT. No 06AAA1

EXCEPT FOR HOLES H24 AND H25

PROTECT THE FASTENERS HEAD AND NUTS WITH MAT. No 06ABA1

DO SEALANT BEAD AROUND PARTS WITH MAT. No 06ABB1

APPLY MAT. No 06ABB1 BETWEEN PARTS

HEAD ON THE VISIBLE SIDE N

INBOARD

OUTBOARD

D_SB_536177_5_CAAC_06_01

Figure A-FCAAC - Sheet 06

Replacement of the Frame foot FR41, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 545

5

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

SERVICE BULLETIN

**CONF 003

FR42

FR47

FR40

FR42

A

B

B

Z140

A

C

D

F

C

D

F

D_SB_536177_5_DAAA_01_00

Figure A-FDAAA - Sheet 01

Replacement of the Frame foot FR42, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 546

5

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

SERVICE BULLETIN

**CONF 003

RH SYMMETRICAL

VIEW LOOKING AFT

LH SHOWN

A A

F

W

D

C

(55)

01 WET INSTALL THE FASTENERS WITH MAT No 06AAA1 EXCEPT FOR HOLES H91 AND H92

PROTECT THE FASTENERS HEAD AND NUTS WITH MAT No 06ABA1

DO SEALANT BEAD AROUND PARTS WITH MAT No 06ABB1

APPLY MAT No 06ABB1 BETWEEN PARTS

01

(56) 56

NOTE:

A A

FR42

INBOARD

OUTBOARD

D_SB_536177_5_DAAA_02_01

Figure A-FDAAA - Sheet 02

Replacement of the Frame foot FR42, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 547

5

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

SERVICE BULLETIN

**CONF 003

H90

H68

H69

H70

H71

H72

H75

H76

H77

H78

H67 H66

H65

H64

H62

H61

H63

H74

H73

H60

H89

H88

H87

H86

H85

H83 H52

H53

H54

H55

H56

H57

H59

H58

STGR36

STGR37

(62) (65)

(63)

(64)

B

B

D

FR42

LH SHOWN

RH SYMMETRICAL

VIEW LOOKING AFT

C

C

NOTE:

FASTENERS NOT AFFECTED

HEAD ON THE VISIBLE SIDE N

NUT

SCREW

NUT

SCREW

ASNA2529Ü3

EN6115V3A6

ASNA2529Ü3

EN6115V3A6

N

(3)(4)

10

9

(3)(4)

10

9

HOLE

SYMBOL ITEM PART NUMBER DESCRIPTION HOLE DIAMETER MIN MAX

NUT

SCREW

ASNA2529Ü3

EN6115V3A9

WET INSTALL THE FASTENERS WITH MAT No 06AAA1 EXCEPT FOR HOLES H91 AND H92

PROTECT THE FASTENERS HEAD AND NUTS WITH MAT No 06ABA1

DO SEALANT BEAD AROUND PARTS WITH MAT No 06ABB1

APPLY MAT No 06ABB1 BETWEEN PARTS

0102 PROTECT THE CUTÜOUT AREA WITH MAT No 04CMA2 AND MAT No 04EAC2

NUT

SCREW

ASNA2529Ü3

EN6115V3A8

5.512 mm

(0.217 in)

5.552 mm

(0.218 in)

E

01

CUTÜOUT 02

N

N

N

(1)(2)

NUT

SCREW

ASNA2529Ü3

EN6115V3A6 (1)

(2)

10

9

33

9

(1) 32(2) 9

5.512 mm

(0.217 in)

5.552 mm

(0.218 in)

5.512 mm

(0.217 in)

5.552 mm

(0.218 in)

5.512 mm

(0.217 in)

5.552 mm

(0.218 in)

5.512 mm

(0.217 in)

5.552 mm

(0.218 in)

F

HEAD ON THE HIDDEN SIDE F

LH

RH

102103

(102)(103)

INBOARD

OUTBOARD

04 REWORK THE SURFACES WITH MAXIMUM OF THE 0.5 mm (0.020 in) DURING THE INSTALLATION OF THE NEW FRAME FOOT

04

04

H84

H51

DD

D

D

D_SB_536177_5_DAAA_03_01

Figure A-FDAAA - Sheet 03

Replacement of the Frame foot FR42, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177REVISION No.: 00 - May 20/15 Page: 548

5

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

SERVICE BULLETIN

**CONF 003

FWD

B B

(62)

(63)

(5)

(4)

(3)

RIVET

NUT

SCREW

NAS1726Ü5E

ASNA2001V5Ü8Y

HOLE

SYMBOL ITEM PART NUMBER DESCRIPTION

HOLE DIAMETER

MIN MAX

(4)

(3)

NUT

SCREW

ASNA2529Ü6

EN6114V6X13

7.102 mm

(0.280 in)

7.141 mm

NUT (0.281 in)

SCREW

ASNA2529Ü5

(3) EN6114V5Y8

N (4)

15

16

9.886 mm

(0.389 in)

9.925 mm

(0.391 in)

4.060 mm

(0.160 in)

4.170 mm

(0.164 in) ASNA2050DXJ4020 N

N

N

19

35

12

13

14

7.102 mm

(0.280 in)

7.141 mm

(0.281 in)

NOTE:

HEAD ON THE VISIBLE SIDE

WET INSTALL THE FASTENERS WITH MAT No 06AAA1 EXCEPT FOR HOLES H91 AND H92

PROTECT THE FASTENERS HEAD AND NUTS WITH MAT No 06ABA1

DO SEALANT BEAD AROUND PARTS WITH MAT No 06ABB1

APPLY MAT No 06ABB1 BETWEEN PARTS

01

N

03 USE EXISTING HOLES IN STRINGERS FOR THE INSTALLATION OF STIFFENERS

01

E 01

H98

H97

H96

H95

H93

H91 H92

H94

H99

H100

H101

H102 (57)

(58)

LH

RH

H79

H80

03

FR42

STGR36

LH

RH

102

103

(102)

(103)

C C

(63)

(65)

(62)

(64)

01

D_SB_536177_5_DAAA_04_00

Figure A-FDAAA - Sheet 04

Replacement of the Frame foot FR42, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 549

5

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

SERVICE BULLETIN

**CONF 003

STGR38

STGR37

H113

H112

H111

H110

H109

H108

H107

H106

H105

H104

H103

FR42

LH SHOWN

RH SYMMETRICAL

VIEW LOOKING AFT FASTENERS NOT AFFECTED

NOTE:

HOLE

SYMBOL ITEM PART NUMBER DESCRIPTION HOLE DIAMETER MIN MAX

8

9 NUT

SCREW

ASNA2529Ü3

EN6115V3A7 (3)

(4)

9

18

NUT

SCREW

ASNA2529Ü3

EN6115V3A4 (3)

(4)

19 RIVET ASNA2050DXJ4020 4.060 mm (0.160 in) 4.170 mm (0.164 in) (5) N

17

9 NUT

SCREW

ASNA2529Ü3

EN6115V3A5 (3)

(4)

WET INSTALL THE FASTENERS WITH MAT No 06AAA1 EXCEPT FOR HOLES H91 AND H92 01

PROTECT THE FASTENERS HEAD AND NUTS WITH MAT No 06ABA1

DO SEALANT BEAD AROUND PARTS WITH MAT No 06ABB1

APPLY MAT No 06ABB1 BETWEEN PARTS

USE EXISTING HOLES IN STRINGERS FOR THE INSTALLATION OF 03

STIFFENERS

HEAD ON THE VISIBLE SIDE

NUT

SCREW

ASNA2529Ü3

EN6115V3A4 (5) 189 5.512 mm (0.217 in) 5.552 mm (0.218 in)

5.512 mm

(0.217 in)

5.552 mm

(0.218 in)

5.512 mm

(0.217 in)

5.552 mm

(0.218 in)

5.512 mm

(0.217 in)

5.552 mm

(0.218 in) N

N

NN

03

F

N

01

G

FR42

FWD

(66)(67)

H115

H116H117

LH

RH

H114

01 G

(66)(67) (68) (69) LH LHRH RH

STGR37

FR42

01

H82

H81

OUTBOARD

INBOARD

E

E

E E

D_SB_536177_5_DAAA_05_01

Figure A-FDAAA - Sheet 05

Replacement of the Frame foot FR42, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177REVISION No.: 00 - May 20/15 Page: 550

5

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

SERVICE BULLETIN

**CONF 002

FR42

FR47

FR40

FR42

A

B

B

Z140

A

C

D

F

C

D

F

D_SB_536177_5_DAAB_01_00

Figure A-FDAAB - Sheet 01

Replacement of the Frame foot FR42, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 551

5

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

SERVICE BULLETIN

**CONF 002

RH SYMMETRICAL

VIEW LOOKING AFT

LH SHOWN

A A

F

W

D

C

(55)

01 WET INSTALL THE FASTENERS WITH MAT No 06AAA1 EXCEPT FOR HOLES H91 AND H92

PROTECT THE FASTENERS HEAD AND NUTS WITH MAT No 06ABA1

DO SEALANT BEAD AROUND PARTS WITH MAT No 06ABB1

APPLY MAT No 06ABB1 BETWEEN PARTS

01

(56) 56

NOTE:

A A

FR42

INBOARD

OUTBOARD

D_SB_536177_5_DAAB_02_01

Figure A-FDAAB - Sheet 02

Replacement of the Frame foot FR42, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 552

5

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

SERVICE BULLETIN

**CONF 002

NOTE:

FASTENERS NOT AFFECTED

HEAD ON THE VISIBLE SIDE N

NUT

SCREW

ASNA2529Ü3

EN6115V3A6 (1)

(2)

10

9 F

HOLE

SYMBOL ITEM PART NUMBER DESCRIPTION HOLE DIAMETER MIN MAX

NUT

SCREW

ASNA2529Ü3

EN6115V3A9

WET INSTALL THE FASTENERS WITH MAT No 06AAA1 EXCEPT FOR HOLES H91 AND H92

PROTECT THE FASTENERS HEAD AND NUTS WITH MAT No 06ABA1

DO SEALANT BEAD AROUND PARTS WITH MAT No 06ABB1

APPLY MAT No 06ABB1 BETWEEN PARTS

0102 PROTECT THE CUTÜOUT AREA WITH MAT No 04CMA2 AND MAT No 04EAC2

NUT

SCREW

ASNA2529Ü3

EN6115V3A8

N

N

N

(1)(2)

NUT

SCREW

ASNA2529Ü3

EN6115V3A6 (1)

(2)

10

9

33

9

(1) 32(2) 9

5.512 mm

(0.217 in)

5.552 mm

(0.218 in)

5.512 mm

(0.217 in)

5.552 mm

(0.218 in)

5.512 mm

(0.217 in)

5.552 mm

(0.218 in)

5.512 mm

(0.217 in)

5.552 mm

(0.218 in)

HEAD ON THE HIDDEN SIDE F

H90

H68

H69

H70

H71

H72

H75

H76

H77

H78

H67 H66

H65

H64

H62

H61

H63

H74

H73

H60

H89

H88

H87

H86

H85

H83 H52

H53

H54

H55

H56

H57

H59

H58

STGR36

STGR37

(62) (65)

(63)

(64)

B

B

D

FR42

LH SHOWN

RH SYMMETRICAL

VIEW LOOKING AFT

C

C

E

01

CUTÜOUT 02

LH

RH

102103

(102)(103)

INBOARD

OUTBOARD

04

04

H84

H51

DD

D

D

04 REWORK THE SURFACES WITH MAXIMUM OF THE 0.5 mm (0.020 in) DURING THE INSTALLATION OF THE NEW FRAME FOOT D_SB_536177_5_DAAB_03_01

Figure A-FDAAB - Sheet 03

Replacement of the Frame foot FR42, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177REVISION No.: 00 - May 20/15 Page: 553

5

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

SERVICE BULLETIN

**CONF 002

FWD

C C

(63)

(65)

(62)

(64)

(5)

(4)

(3)

RIVET

NUT

SCREW

NAS1726Ü5E

ASNA2001V5Ü8Y

HOLE

SYMBOL ITEM PART NUMBER DESCRIPTION

HOLE DIAMETER

MIN MAX

(2)

(1)

NUT

SCREW

ASNA2529Ü6

EN6114V6Y13

8.692 mm

(0.342 in)

8.732 mm

NUT (0.344 in)

SCREW

ASNA2529Ü5

(1) EN6114V5Y8

(2)

10.282 mm

(0.405 in)

10.321 mm

(0.406 in)

4.060 mm

(0.160 in)

4.170 mm

(0.164 in) ASNA2050DXJ4020 N

N

15

16

19

34

12

13

14

NOTE:

HEAD ON THE VISIBLE SIDE

WET INSTALL THE FASTENERS WITH MAT No 06AAA1 EXCEPT FOR HOLES H91 AND H92

PROTECT THE FASTENERS HEAD AND NUTS WITH MAT No 06ABA1

DO SEALANT BEAD AROUND PARTS WITH MAT No 06ABB1

APPLY MAT No 06ABB1 BETWEEN PARTS

01

N

03 USE EXISTING HOLES IN STRINGERS FOR THE INSTALLATION OF STIFFENERS

01

E 01

N

N

8.692 mm

(0.342 in)

8.732 mm

(0.344 in)

H98

H97

H96

H95

H93

H91 H92

H94

H99

H100

H101

H102

B B

(62)

(63)

01

(58)

(57)

LH

RH

H79

H80

03

FR42

STGR36

LH

RH

102

103

(102)

(103)

ELECTRICAL BONDING

05 SPOTFACES TO BE REALIZED DURING INSTALLATION AFTER DRILLING OF PARTS TO DIAMETER 27 mm

(1.063 in) FOR OLD FASTENERS DIAMETER 9.52 mm (0.375 in) AND TO DIAMETER 29 mm (1.142 in)

FOR OLD FASTENERS DIAMETER 11.1 mm (0.437 in)

05

TYPICAL SECTION

FRAME FOOT

05

D D

D_SB_536177_5_DAAB_04_01

Figure A-FDAAB - Sheet 04

Replacement of the Frame foot FR42, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 554

5

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

SERVICE BULLETIN

**CONF 002

FASTENERS NOT AFFECTED

NOTE:

HOLE

SYMBOL ITEM PART NUMBER DESCRIPTION HOLE DIAMETER MIN MAX

8

9 NUT

SCREW

ASNA2529Ü3

EN6115V3A7 (3)

(4)

9

18

NUT

SCREW

ASNA2529Ü3

EN6115V3A4 (3)

(4)

19 RIVET ASNA2050DXJ4020 4.060 mm (0.160 in) 4.170 mm (0.164 in) (5) N

17

9 NUT

SCREW

ASNA2529Ü3

EN6115V3A5 (3)

(4)

WET INSTALL THE FASTENERS WITH MAT No 06AAA1 EXCEPT FOR HOLES H91 AND H92 01

PROTECT THE FASTENERS HEAD AND NUTS WITH MAT No 06ABA1

DO SEALANT BEAD AROUND PARTS WITH MAT No 06ABB1

APPLY MAT No 06ABB1 BETWEEN PARTS

USE EXISTING HOLES IN STRINGERS FOR THE INSTALLATION OF 03

STIFFENERS

HEAD ON THE VISIBLE SIDE

NUT

SCREW

ASNA2529Ü3

EN6115V3A4 (5) 189 5.512 mm (0.217 in) 5.552 mm (0.218 in)

5.512 mm

(0.217 in)

5.552 mm

(0.218 in)

5.512 mm

(0.217 in)

5.552 mm

(0.218 in)

5.512 mm

(0.217 in)

5.552 mm

(0.218 in) N

N

NN

N

STGR38

STGR37

H113

H112

H111

H110

H109

H108

H107

H106

H105

H104

H103

FR42

LH SHOWN

RH SYMMETRICAL

VIEW LOOKING AFT

03

F 01

G

FR42

FWD

(66)(67)

H115

H116

H117

LH

RH

H114

01 G (66) (67) (68) (69) LH LHRH RH

STGR37

FR42

01

H82

H81

OUTBOARD

INBOARD

E

E

E E

D_SB_536177_5_DAAB_05_01

Figure A-FDAAB - Sheet 05

Replacement of the Frame foot FR42, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177REVISION No.: 00 - May 20/15 Page: 555

5

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

SERVICE BULLETIN

**CONF 001

FR40

A

B

FR42

FR47

FR42

B

Z140

A

C

D

F

C

D

F

D_SB_536177_5_DAAC_01_00

Figure A-FDAAC - Sheet 01

Replacement of the Frame foot FR42, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 556

5

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

SERVICE BULLETIN

**CONF 001

RH SYMMETRICAL

VIEW LOOKING AFT

LH SHOWN

A A

F

W

D

C

(55)

01 WET INSTALL THE FASTENERS WITH MAT No 06AAA1 EXCEPT FOR HOLES H91 AND H92

PROTECT THE FASTENERS HEAD AND NUTS WITH MAT No 06ABA1

DO SEALANT BEAD AROUND PARTS WITH MAT No 06ABB1

APPLY MAT No 06ABB1 BETWEEN PARTS

01

(56) 56

NOTE:

A A

FR42

INBOARD

OUTBOARD

D_SB_536177_5_DAAC_02_01

Figure A-FDAAC - Sheet 02

Replacement of the Frame foot FR42, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 557

5

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

SERVICE BULLETIN

**CONF 001

D FASTENERS NOT AFFECTED NOTE:

FR42

LH SHOWN

RH SYMMETRICAL

VIEW LOOKING AFT

WET INSTALL THE FASTENERS WITH MAT No 06AAA1 EXCEPT FOR HOLES H91 AND H92 01

PROTECT THE FASTENERS HEAD AND NUTS WITH MAT No 06ABA1

DO SEALANT BEAD AROUND PARTS WITH MAT No 06ABB1

APPLY MAT No 06ABB1 BETWEEN PARTS

01

03

03

H90

H68

H69

H70

H71

H72

H75

H76

H77

H78

H67 H66 H65

H64

H62

H61

H63

H74

H73

H60

H89

H88

H87

H86

H85

H83 H52

H53

H54

H55

H56

H57

H59

H58

STGR36

STGR37

LH

RH

102103

H84

H51

B

B

E

(102)(103)

INBOARD

OUTBOARD

03 REWORK THE SURFACES WITH MAXIMUM OF THE 0.5 mm (0.020 in) DURING THE INSTALLATION OF THE NEW FRAME FOOT

C

C

C

C

D_SB_536177_5_DAAC_03_01

Figure A-FDAAC - Sheet 03

Replacement of the Frame foot FR42, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177REVISION No.: 00 - May 20/15 Page: 558

5

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

SERVICE BULLETIN

**CONF 001

NOTE:

HOLE

SYMBOL ITEM PART NUMBER DESCRIPTION

HOLE DIAMETER

MIN MAX

9

25

NUT

SCREW

ASNA2529Ü3

EN6115V3X6 5.113 mm

(0.201 in)

5.152 mm

(0.203 in) (5)

HEAD ON THE VISIBLE SIDE

9

25

NUT

SCREW

ASNA2529Ü3

EN6115V3X6 5.113 mm

(0.201 in)

5.152 mm

(0.203 in)

(6)

(7)

9

25

NUT

SCREW

ASNA2529Ü3

EN6115V3X6 5.113 mm

(0.201 in)

5.152 mm

(0.203 in)

(3)

(4)

9

24

NUT

SCREW

ASNA2529Ü3

EN6115V3X7 5.113 mm

(0.201 in)

5.152 mm

(0.203 in)

(3)

(4)

9

25

NUT

SCREW

ASNA2529Ü3

EN6115V3X6 5.113 mm

(0.201 in)

5.152 mm

(0.203 in)

(3)

(4)

N

N

N

N

F

HEAD ON THE HIDDEN SIDE F

N

9

23

NUT

SCREW

ASNA2529Ü3

EN6115V3X5 5.113 mm

(0.201 in)

5.152 mm

(0.203 in) (5)

9

23

NUT

SCREW

ASNA2529Ü3

EN6115V3X5 5.113 mm

(0.201 in)

5.152 mm

(0.203 in)

(6)

(7)

OR

OR

D_SB_536177_5_DAAC_04_00

Figure A-FDAAC - Sheet 04

Replacement of the Frame foot FR42, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 559

5

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

SERVICE BULLETIN

**CONF 001

FWD

B B

102

103

LH

RH

(58)

(57)

LH

RH

H79

H80 FR42

NOTE:

HOLE

SYMBOL ITEM PART NUMBER DESCRIPTION

HOLE DIAMETER

MIN MAX

HEAD ON THE VISIBLE SIDE

14

27

NUT

SCREW

NAS1726Ü5E

ASNA2001V5Ü8X 8.296 mm

(0.327 in)

8.335 mm

(0.328 in)

(3)

(4)

16

28

NUT

SCREW

ASNA2529Ü5

EN6114V5X8 8.296 mm

(0.327 in)

8.335 mm

(0.328 in)

(3)

(4)

19 ASNA2050DXJ4020 RIVET 4.060 mm

(0.160 in)

4.170 mm

(0.164 in) (19)

N

12

35

NUT

SCREW

ASNA2529Ü6

EN6114V6X13 9.886 mm

(0.389 in)

9.925 mm

(0.391 in)

(3)

(4)

01 WET INSTALL THE FASTENERS WITH MAT No 06AAA1 EXCEPT FOR HOLES H91 AND H92

PROTECT THE FASTENERS HEAD AND NUTS WITH MAT No 06ABA1

DO SEALANT BEAD AROUND PARTS WITH MAT No 06ABB1

APPLY MAT No 06ABB1 BETWEEN PARTS

02 USE EXISTING HOLES IN STRINGERS FOR THE INSTALLATION OF STIFFENERS

STIFFENERS

02

E 01

01

N

N

N

N

STGR36

H98

H97

H96

H95

H93

H91 H92

H94

H99

H100

H101

H102

(102)

(103)

04

TYPICAL SECTION

FRAME FOOT

04

C C

ELECTRICAL BONDING

04 SPOTFACES TO BE REALIZED DURING INSTALLATION AFTER DRILLING OF PARTS TO DIAMETER 27 mm

(1.063 in) FOR OLD FASTENERS DIAMETER 9.52 mm (0.375 in) AND TO DIAMETER 29 mm (1.142 in)

FOR OLD FASTENERS DIAMETER 11.1 mm (0.437 in) D_SB_536177_5_DAAC_05_01

Figure A-FDAAC - Sheet 05

Replacement of the Frame foot FR42, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 560

5

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

SERVICE BULLETIN

**CONF 001

(66)

(67) (68)

(69)

H113

STGR37

STGR38

FR42

FWD

(66)

(67)

H112

H111

H110

H109

H108

H107

H106

H105

H104

H103

H117

H116

H115

LH LH

LH

RH

RH RH

STGR37

FR42

FASTENERS NOT AFFECTED

NOTE:

FR42

RH SYMMETRICAL

VIEW LOOKING AFT

LH SHOWN

H114

HOLE

SYMBOL ITEM PART NUMBER DESCRIPTION

HOLE DIAMETER

MIN MAX

9

23

NUT

SCREW

ASNA2529Ü3

EN6115V3X5 5.113 mm

(0.201 in)

5.152 mm

(0.203 in)

(3)

(4)

5.113 mm

(0.201 in)

5.152 mm

(0.203 in)

9

29

NUT

SCREW

ASNA2529Ü3

EN6115V3X4 5.113 mm

(0.201 in)

5.152 mm

(0.203 in)

(3)

(4)

01 WET INSTALL THE FASTENERS WITH MAT. No 06AAA1 EXCEPT FOR HOLES H91 AND H92

PROTECT THE FASTENERS HEAD AND NUTS WITH MAT No 06ABA1

DO SEALANT BEAD AROUND PARTS WITH MAT. No 06ABB1

APPLY MAT. No 06ABB1 BETWEEN PARTS

02 USE EXISTING HOLES IN STRINGERS FOR THE INSTALLATION OF

STIFFENERS

HEAD ON THE VISIBLE SIDE

HEAD ON THE HIDDEN SIDE F

N

9

29

NUT

SCREW

ASNA2529Ü3

EN6115V3X4

5.113 mm

(0.201 in)

5.152 mm

9 (0.203 in)

24

NUT

SCREW

ASNA2529Ü3

(3) EN6115V3X7

(4)

19 ASNA2050DXJ4020 RIVET 4.060 mm

(0.160 in)

4.170 mm

(0.164 in) (19)

G

(19)

02 01

01

N

F

N

N

N

01

F

G

OUTBOARD

INBOARD

D

D

D D

D_SB_536177_5_DAAC_06_01

Figure A-FDAAC - Sheet 06

Replacement of the Frame foot FR42, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 561

5

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

SERVICE BULLETIN

**CONF 003

FR40

A

B

FR47

FR43

B

Z140

A

C

D

F

C

D

F

FR43

D_SB_536177_5_EAAA_01_00

Figure A-FEAAA - Sheet 01

Replacement of the Frame foot FR43, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 562

5

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

SERVICE BULLETIN

**CONF 003

RH SYMMETRICAL

VIEW LOOKING AFT

LH SHOWN

A A

F

W

D

C

(55)

01 WET INSTALL THE FASTENERS WITH MAT. No 06AAA1 EXCEPT FOR HOLES H150 AND H151

PROTECT THE FASTENERS HEAD AND NUTS WITH MAT. No 06ABA1

DO SEALANT BEAD AROUND PARTS WITH MAT. No 06ABB1

APPLY MAT. No 06ABB1 BETWEEN PARTS

01

(56) 56

NOTE:

A A

FR43

INBOARD

OUTBOARD

D_SB_536177_5_EAAA_02_01

Figure A-FEAAA - Sheet 02

Replacement of the Frame foot FR43, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 563

5

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

SERVICE BULLETIN

**CONF 003

WET INSTALL THE FASTENERS WITH MAT. No 06AAA1 EXCEPT FOR HOLES H150 AND H151 01

PROTECT THE FASTENERS HEAD AND NUTS WITH MAT. No 06ABA1

DO SEALANT BEAD AROUND PARTS WITH MAT. No 06ABB1

APPLY MAT. No 06ABB1 BETWEEN PARTS

FASTENERS NOT AFFECTED

NOTE:

D

RH SYMMETRICAL

VIEW LOOKING AFT

LH SHOWN

FR43

(72)(71)

(70)

LH

RH

STGR36

LHRH

H136

H135

H134

H149

H148

H147

H146

H145 H122

H124

H126

H132

H128

H131

H121

H123

H125

H127

H133

H129

H130

H140

H141

H142

H143

H144

E

01

01

PROTECT THE CUTÜOUT AREA WITH MAT. No 04CMA2 AND MAT. No 04EAC2 02

02

CUTÜOUT HOLE

SYMBOL ITEM PART NUMBER DESCRIPTION HOLE DIAMETER MIN MAX

HEAD ON THE VISIBLE SIDE

5.512 mm

(0.217 in)

5.552 mm

(0.218 in) (2) NUT ASNA2529Ü3

(1) SCREW EN6115V3A5

9

17

5.512 mm

(0.217 in)

5.552 mm

(0.218 in) (2) NUT ASNA2529Ü3

(1) SCREW EN6115V3A6 10

9

5.512 mm

(0.217 in)

5.552 mm

(0.218 in) (2) NUT ASNA2529Ü3

(1) SCREW EN6115V3A3

9

36

HEAD ON THE HIDDEN SIDE

N

F

5.512 mm

(0.217 in)

5.552 mm

(0.218 in) (2) NUT ASNA2529Ü3

(1) SCREW EN6115V3A7 8

9

5.512 mm

(0.217 in)

5.552 mm

(0.218 in) (4) NUT ASNA2529Ü3

(3) SCREW EN6115V3A6 10

9

5.512 mm

(0.217 in)

5.552 mm

(0.218 in) (4) NUT ASNA2529Ü3

(3) SCREW EN6115V3A8 32

9

5.512 mm

(0.217 in)

5.552 mm

(0.218 in) (2) NUT ASNA2529Ü3

(1) SCREW EN6115V3A7 8

9

NNNN

FFF

(104) 104

(105) 105

OUTBOARD

INBOARD

FR43

REWORK THE SURFACES WITH MAXIMUM OF THE 0.5 mm (0.020 in) DURING THE INSTALLATION OF THE NEW FRAME FOOT 04

D_SB_536177_5_EAAA_03_01

C

C

B

B

B B

D

D

04

04

04

D

D

D_SB_536177_5_EAAA_03_01

Figure A-FEAAA - Sheet 03

Replacement of the Frame foot FR43, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177REVISION No.: 00 - May 20/15 Page: 564

5

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

SERVICE BULLETIN

**CONF 003

(58)

(57)

LH

RH

9.886 mm

(0.389 in)

9.925 mm

NUT (0.391 in)

SCREW

ASNA2529Ü6

EN6114V6X14

HOLE

SYMBOL ITEM PART NUMBER DESCRIPTION

HOLE DIAMETER

MIN MAX

HEAD ON THE VISIBLE SIDE

NOTE:

12

26

N

8.692 mm

(0.342 in)

8.732 mm

NUT (0.345 in)

SCREW

NAS1726Ü5E

ASNA2001V5Ü8Y

14

13

8.692 mm

(0.342 in)

8.732 mm

NUT (0.345 in)

SCREW

ASNA2529Ü5

EN6114V5Y8

16

15

4.060 mm

(0.160 in)

4.170 mm

(0.164 in) (5) 19 ASNA2050DXJ4020 RIVET

03 USE EXISTING HOLES IN STRINGERS FOR THE INSTALLATION OF STIFFENERS

01 WET INSTALL THE FASTENERS WITH MAT. No 06AAA1 EXCEPT FOR HOLES H150 AND H151

PROTECT THE FASTENERS HEAD AND NUTS WITH MAT. No 06ABA1

DO SEALANT BEAD AROUND PARTS WITH MAT. No 06ABB1, APPLY MAT. No 06ABB1 BETWEEN PARTS

03

N

(4)

(3)

(4)

(3)

(4)

(3)

N

N

N

LH

RH

(104) 104

(105) 105

FWD

E 01

H154 H156

H155 H157

H152 H153

H150 H151 FR43

STGR36

H169

H168

01

05 05

FRAME FOOT

D D

C C

TYPICAL SECTION

05 SPOTFACES TO BE REALIZED DURING INSTALLATION AFTER DRILLING OF PARTS TO DIAMETER 27 mm

(1.063 in) FOR OLD FASTENERS DIAMETER 9.52 mm (0.375 in) AND TO DIAMETER 29 mm (1.142 in)

 FOR OLD FASTENERS DIAMETER 11.1 mm (0.437 in)

ELECTRICAL BONDING

D_SB_536177_5_EAAA_04_01

Figure A-FEAAA - Sheet 04

Replacement of the Frame foot FR43, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 565

5

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

SERVICE BULLETIN

**CONF 003

FASTENERS NOT AFFECTED

STGR38

STGR37

NOTE:

H163

H162

H161

H160

H159

H158

H139

H138

H137

FR43

RH SYMMETRICAL

VIEW LOOKING AFT

LH SHOWN

5.512 mm

(0.217 in)

5.552 mm

NUT (0.218 in)

SCREW

ASNA2529Ü3

EN6115V3A9

HOLE

SYMBOL ITEM PART NUMBER DESCRIPTION

HOLE DIAMETER

MIN MAX

HEAD ON THE VISIBLE SIDE

9

33

N

5.512 mm

(0.217 in)

5.552 mm

NUT (0.218 in)

SCREW

ASNA2529Ü3

EN6115V3A7

9

8

5.512 mm

(0.217 in)

5.552 mm

NUT (0.218 in)

SCREW

ASNA2529Ü3

EN6115V3A8

9

32

5.512 mm

(0.217 in)

5.552 mm

(0.218 in)

01 WET INSTALL THE FASTENERS WITH MAT No 06AAA1 EXCEPT FOR HOLES H150 AND H151

PROTECT THE FASTENERS HEAD AND NUTS WITH MAT No 06ABA1

DO SEALANT BEAD AROUND PARTS WITH MAT No 06ABB1

APPLY MAT No 06ABB1 BETWEEN PARTS

(4)

(3)

(4)

(3)

(4)

(3)

G

F

NUT

SCREW

ASNA2529Ü3

EN6115V3A5

9

17

(4)

(3)

HEAD ON THE HIDDEN SIDE F

01

F

F

F

N

FR43

FWD

(72)

(71)

H167

H166

H165

LH

RH

H164

G 01

OUTBOARD

INBOARD

D_SB_536177_5_EAAA_05_00

Figure A-FEAAA - Sheet 05

Replacement of the Frame foot FR43, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 566

5

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

SERVICE BULLETIN

**CONF 002

FR40

A

B

FR47

FR43

B

Z140

A

C

D

F

C

D

F

FR43

D_SB_536177_5_EAAB_01_00

Figure A-FEAAB - Sheet 01

Replacement of the Frame foot FR43, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 567

5

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

SERVICE BULLETIN

**CONF 002

RH SYMMETRICAL

VIEW LOOKING AFT

LH SHOWN

A A

F

W

D

C

(55)

01 WET INSTALL THE FASTENERS WITH MAT. No 06AAA1 EXCEPT FOR HOLES H150 AND H151

PROTECT THE FASTENERS HEAD AND NUTS WITH MAT. No 06ABA1

DO SEALANT BEAD AROUND PARTS WITH MAT. No 06ABB1

APPLY MAT. No 06ABB1 BETWEEN PARTS

01

(56) 56

NOTE:

A A

FR43

INBOARD

OUTBOARD

D_SB_536177_5_EAAB_02_01

Figure A-FEAAB - Sheet 02

Replacement of the Frame foot FR43, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 568

5

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

SERVICE BULLETIN

**CONF 002

WET INSTALL THE FASTENERS WITH MAT. No 06AAA1 EXCEPT FOR HOLES H150 AND H151 01

PROTECT THE FASTENERS HEAD AND NUTS WITH MAT. No 06ABA1

DO SEALANT BEAD AROUND PARTS WITH MAT. No 06ABB1

APPLY MAT. No 06ABB1 BETWEEN PARTS

FASTENERS NOT AFFECTED

NOTE:

D

RH SYMMETRICAL

VIEW LOOKING AFT

LH SHOWN

FR43

(72)(71)

(70)

LH

RH

STGR36

LHRH

H136

H135

H134

H149

H148

H147

H146

H145 H122

H124

H126

H132

H128

H131

H121

H123

H125

H127

H133

H129

H130

H140

H141

H142

H143

H144

E

01

01

PROTECT THE CUTÜOUT AREA WITH MAT. No 04CMA2 AND MAT. No 04EAC2 02

02

CUTÜOUT

HEAD ON THE VISIBLE SIDEHEAD ON THE HIDDEN SIDE

N

F

(104) 104

(105) 105

OUTBOARD

INBOARD

FR43

REWORK THE SURFACES WITH MAXIMUM OF THE 0.5 mm (0.020 in) DURING THE INSTALLATION OF THE NEW FRAME FOOT 04

C

C

B

B

B B

D

D

04

04

04

HOLE

SYMBOL ITEM PART NUMBER DESCRIPTION HOLE DIAMETER MIN MAX

5.512 mm

(0.217 in)

5.552 mm

(0.218 in) (2) NUT ASNA2529Ü3

(1) SCREW EN6115V3A5

9

17

5.512 mm

(0.217 in)

5.552 mm

(0.218 in) (2) NUT ASNA2529Ü3

(1) SCREW EN6115V3A6 10

9

5.512 mm

(0.217 in)

5.552 mm

(0.218 in) (2) NUT ASNA2529Ü3

(1) SCREW EN6115V3A3

9

36

5.512 mm

(0.217 in)

5.552 mm

(0.218 in) (2) NUT ASNA2529Ü3

(1) SCREW EN6115V3A7 8

9

5.512 mm

(0.217 in)

5.552 mm

(0.218 in) (2) NUT ASNA2529Ü3

(1) SCREW EN6115V3A6 10

9

5.512 mm

(0.217 in)

5.552 mm

(0.218 in) (2) NUT ASNA2529Ü3

(1) SCREW EN6115V3A8 32

9

5.512 mm

(0.217 in)

5.552 mm

(0.218 in) (2) NUT ASNA2529Ü3

(1) SCREW EN6115V3A7 8

9

NNNN

FFF

D

D

D_SB_536177_5_EAAB_03_02

Figure A-FEAAB - Sheet 03

Replacement of the Frame foot FR43, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177REVISION No.: 00 - May 20/15 Page: 569

5

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

SERVICE BULLETIN

**CONF 002

(58)

(57)

LH

RH

HEAD ON THE VISIBLE SIDE

NOTE:

N

03 USE EXISTING HOLES IN STRINGERS FOR THE INSTALLATION OF STIFFENERS

01 WET INSTALL THE FASTENERS WITH MAT. No 06AAA1 EXCEPT FOR HOLES H150 AND H151

PROTECT THE FASTENERS HEAD AND NUTS WITH MAT. No 06ABA1

DO SEALANT BEAD AROUND PARTS WITH MAT. No 06ABB1, APPLY MAT. No 06ABB1 BETWEEN PARTS

03

LH

RH

(104) 104

(105) 105

FWD

E 01

H154 H156

H155 H157

H152 H153

H150 H151 FR43

STGR36

H169

H168

01

05 05

FRAME FOOT

D D

C C

TYPICAL SECTION

05 SPOTFACES TO BE REALIZED DURING INSTALLATION AFTER DRILLING OF PARTS TO DIAMETER 27 mm

(1.063 in) FOR OLD FASTENERS DIAMETER 9.52 mm (0.375 in) AND TO DIAMETER 29 mm (1.142 in)

 FOR OLD FASTENERS DIAMETER 11.1 mm (0.437 in)

ELECTRICAL BONDING

10.282 mm

(0.405 in)

10.321 mm

NUT (0.406 in)

SCREW

ASNA2529Ü6

EN6114V6Y14

HOLE

SYMBOL ITEM PART NUMBER DESCRIPTION

HOLE DIAMETER

MIN MAX

12

11

8.692 mm

(0.342 in)

8.732 mm

NUT (0.345 in)

SCREW

NAS1726Ü5E

ASNA2001V5Ü8Y

14

13

8.692 mm

(0.342 in)

8.732 mm

NUT (0.345 in)

SCREW

ASNA2529Ü5

EN6114V5Y8

16

15

4.060 mm

(0.160 in)

4.170 mm

(0.164 in) (5) 19 ASNA2050DXJ4020 RIVET N

(2)

(1)

(4)

(3)

(2)

(1)

N

N

N

D_SB_536177_5_EAAB_04_01

Figure A-FEAAB - Sheet 04

Replacement of the Frame foot FR43, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 570

5

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

SERVICE BULLETIN

**CONF 002

FASTENERS NOT AFFECTED

STGR38

STGR37

NOTE:

H163

H162

H161

H160

H159

H158

H139

H138

H137

FR43

RH SYMMETRICAL

VIEW LOOKING AFT

LH SHOWN

5.512 mm

(0.217 in)

5.552 mm

NUT (0.218 in)

SCREW

ASNA2529Ü3

EN6115V3A9

HOLE

SYMBOL ITEM PART NUMBER DESCRIPTION

HOLE DIAMETER

MIN MAX

HEAD ON THE VISIBLE SIDE

9

33

N

5.512 mm

(0.217 in)

5.552 mm

NUT (0.218 in)

SCREW

ASNA2529Ü3

EN6115V3A7

9

8

5.512 mm

(0.217 in)

5.552 mm

NUT (0.218 in)

SCREW

ASNA2529Ü3

EN6115V3A8

9

32

5.512 mm

(0.217 in)

5.552 mm

(0.218 in)

01 WET INSTALL THE FASTENERS WITH MAT No 06AAA1 EXCEPT FOR HOLES H150 AND H151

PROTECT THE FASTENERS HEAD AND NUTS WITH MAT No 06ABA1

DO SEALANT BEAD AROUND PARTS WITH MAT No 06ABB1

APPLY MAT No 06ABB1 BETWEEN PARTS

(2)

(1)

(2)

(1)

(2)

(1)

G

F

NUT

SCREW

ASNA2529Ü3

EN6115V3A5

9

17

(2)

(1)

HEAD ON THE HIDDEN SIDE F

01

F

F

F

N

FR43

FWD

(72)

(71)

H167

H166

H165

LH

RH

H164

G 01

OUTBOARD

INBOARD

D_SB_536177_5_EAAB_05_00

Figure A-FEAAB - Sheet 05

Replacement of the Frame foot FR43, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 571

5

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

SERVICE BULLETIN

**CONF 001

FR40

A

B

FR47

FR43

B

Z140

A

C

D

F

C

D

F

FR43

D_SB_536177_5_EAAC_01_00

Figure A-FEAAC - Sheet 01

Replacement of the Frame foot FR43, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 572

5

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

SERVICE BULLETIN

**CONF 001

RH SYMMETRICAL

VIEW LOOKING AFT

LH SHOWN

A A

F

W

D

C

(55)

01 WET INSTALL THE FASTENERS WITH MAT. No 06AAA1 EXCEPT FOR HOLES H150 AND H151

PROTECT THE FASTENERS HEAD AND NUTS WITH MAT. No 06ABA1

DO SEALANT BEAD AROUND PARTS WITH MAT. No 06ABB1

APPLY MAT. No 06ABB1 BETWEEN PARTS

01

(56) 56

NOTE:

A A

FR43

INBOARD

OUTBOARD

D_SB_536177_5_EAAC_02_01

Figure A-FEAAC - Sheet 02

Replacement of the Frame foot FR43, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 573

5

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

SERVICE BULLETIN

**CONF 001

D

RH SYMMETRICAL

VIEW LOOKING AFT

LH SHOWN

FR43

LH

RH

(104)

(105)

H18

H14

H13

H12

H19

H10 H11

H23

H22

H21

H20

H15

H16

H17

H8

H6

H4

H2 H1

H3

H5

H7

H9

STGR36

E

01 WET INSTALL THE FASTENERS WITH MAT. No 06AAA1 EXCEPT FOR HOLES H150 AND H151

PROTECT THE FASTENERS HEAD AND NUTS WITH MAT. No 06ABA1

DO SEALANT BEAD AROUND PARTS WITH MAT No 06ABB1

NOTE:

FASTENERS NOT AFFECTED

104

105

01

INBOARD

OUTBOARD

03

03

03

B

B

C

C

03 REWORK THE SURFACES WITH MAXIMUM OF THE 0.5 mm (0.020 in)

DURING THE INSTALLATION OF THE NEW FRAME FOOT

C

C

APPLY MAT. No 06ABB1 BETWEEN PARTS

H136

H135

H134

H149

H148

H146

H145 H122

H124

H126

H132

H128

H131

H121

H123

H125

H127

H133

H129

H130

H140

H141

H142

H143

H144

H147

D_SB_536177_5_EAAC_03_01

Figure A-FEAAC - Sheet 03

Replacement of the Frame foot FR43, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 574

5

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

SERVICE BULLETIN

**CONF 001

5.113 mm

(0.201 in)

5.113 mm

(0.201 in)

5.152 mm

(0.203 in)

5.152 mm

(0.203 in) (5)

(7)

NUT

SCREW

NUT

ASNA2529Ü3

EN6115V3X5

ASNA2529Ü3

HOLE

SYMBOL ITEM PART NUMBER DESCRIPTION

HOLE DIAMETER

MIN MAX

(6) EN6115V3X5 SCREW

HEAD ON THE VISIBLE SIDE

NOTE:

9

23

9

23

5.113 mm

(0.201 in)

5.113 mm

(0.201 in)

5.152 mm

(0.203 in)

5.152 mm

(0.203 in) (5)

(7)

NUT

SCREW

NUT

ASNA2529Ü3

EN6115V3X6

ASNA2529Ü3

(6) EN6115V3X6 SCREW

9

25

9

25

5.113 mm

(0.201 in)

5.113 mm

(0.201 in)

5.152 mm

(0.203 in)

5.152 mm

(0.203 in) (5)

(7)

NUT

SCREW

NUT

ASNA2529Ü3

EN6115V3X7

ASNA2529Ü3

(6) EN6115V3X7 SCREW

9

24

9

24

5.113 mm

(0.201 in)

5.152 mm

(4) ASNA2529Ü3 NUT (0.203 in)

(3) EN6115V3X9 SCREW

9

39

5.113 mm

(0.201 in)

5.152 mm

(4) ASNA2529Ü3 NUT (0.203 in)

(3) EN6115V3X6 SCREW

9

25

5.113 mm

(0.201 in)

5.152 mm

(4) ASNA2529Ü3 NUT (0.203 in)

(3) EN6115V3X8 SCREW

9

40

N

N

N

F

F

F

OR

OR

OR

HEAD ON THE HIDDEN SIDE F

N

D_SB_536177_5_EAAC_04_00

Figure A-FEAAC - Sheet 04

Replacement of the Frame foot FR43, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 575

5

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

SERVICE BULLETIN

**CONF 001

(58)

(57)

LH

RH

HEAD ON THE VISIBLE SIDE

NOTE:

N

02 USE EXISTING HOLES IN STRINGERS FOR THE INSTALLATION OF STIFFENERS

01 WET INSTALL THE FASTENERS WITH MAT. No 06AAA1 EXCEPT FOR HOLES H150 AND H151

PROTECT THE FASTENERS HEAD AND NUTS WITH MAT. No 06ABA1

DO SEALANT BEAD AROUND PARTS WITH MAT. No 06ABB1, APPLY MAT. No 06ABB1 BETWEEN PARTS

02

LH

RH

(104) 104

(105) 105

FWD

E 01

H154 H156

H155 H157

H152 H153

H150 H151 FR43

STGR36

H169

H168

01

04 04

FRAME FOOT

TYPICAL SECTION

04 SPOTFACES TO BE REALIZED DURING INSTALLATION AFTER DRILLING OF PARTS TO DIAMETER 27 mm

(1.063 in) FOR OLD FASTENERS DIAMETER 9.52 mm (0.375 in) AND TO DIAMETER 29 mm (1.142 in)

 FOR OLD FASTENERS DIAMETER 11.1 mm (0.437 in)

ELECTRICAL BONDING

B B

C C

9.886 mm

(0.389 in)

9.925 mm

NUT (0.391 in)

SCREW

ASNA2529Ü6

EN6114V6X14

HOLE

SYMBOL ITEM PART NUMBER DESCRIPTION

HOLE DIAMETER

MIN MAX

12

26

8.296 mm

(0.327 in)

8.335 mm

NUT (0.328 in)

SCREW

NAS1726Ü5E

ASNA2001V5Ü8X

14

27

8.296 mm

(0.327 in)

8.335 mm

NUT (0.328 in)

SCREW

ASNA2529Ü5

EN6114V5X8

16

28

4.060 mm

(0.160 in)

4.170 mm

(0.164 in) (19) 19 ASNA2050DXJ4020 RIVET

N

N

N

N

(4)

(3)

(4)

(3)

(4)

(3)

D_SB_536177_5_EAAC_05_01

Figure A-FEAAC - Sheet 05

Replacement of the Frame foot FR43, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 576

5

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

SERVICE BULLETIN

**CONF 001

FASTENERS NOT AFFECTED

STGR38

STGR37

NOTE:

H163

H162

H161

H160

H159

H158

H139

H138

H137

FR43

RH SYMMETRICAL

VIEW LOOKING AFT

LH SHOWN

5.113 mm

(0.201 in)

5.152 mm

NUT (0.203 in)

SCREW

ASNA2529Ü3

EN6115V3X9

HOLE

SYMBOL ITEM PART NUMBER DESCRIPTION

HOLE DIAMETER

MIN MAX

HEAD ON THE VISIBLE SIDE

9

39

N

5.113 mm

(0.201 in)

5.152 mm

NUT (0.203 in)

SCREW

ASNA2529Ü3

EN6115V3X7

9

24

5.113 mm

(0.201 in)

5.152 mm

NUT (0.203 in)

SCREW

ASNA2529Ü3

EN6115V3X8

9

40

5.113 mm

(0.201 in)

5.152 mm

(0.203 in)

01 WET INSTALL THE FASTENERS WITH MAT No 06AAA1 EXCEPT FOR HOLES H150 AND H151

PROTECT THE FASTENERS HEAD AND NUTS WITH MAT No 06ABA1

DO SEALANT BEAD AROUND PARTS WITH MAT No 06ABB1

APPLY MAT No 06ABB1 BETWEEN PARTS

(4)

(3)

(4)

(3)

(4)

(3)

G

F

NUT

SCREW

ASNA2529Ü3

EN6115V3X5

9

23

(4)

(3)

HEAD ON THE HIDDEN SIDE F

F

F

F

N

01

FR43

FWD

(72)

(71)

LH

RH

G 01

H167

H166

H165

H164

OUTBOARD

INBOARD

D_SB_536177_5_EAAC_06_00

Figure A-FEAAC - Sheet 06

Replacement of the Frame foot FR43, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 577

5

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

SERVICE BULLETIN

**CONF 003

F D

F

D

C

C

FR44

FR44

A

B

B

Z140

A

FR40

FR47

D_SB_536177_5_GAAA_01_00

Figure A-FGAAA - Sheet 01

Replacement of the Frame foot FR44, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 578

5

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

SERVICE BULLETIN

**CONF 003

NOTE:

01 WET INSTALL THE FASTENERS WITH MAT No 06AAA1 EXCEPT FOR HOLES H203 AND H204

PROTECT THE FASTENERS HEAD AND NUTS WITH MAT No 06ABA1

DO SEALANT BEAD AROUND PARTS WITH MAT No 06ABB1

APPLY MAT No 06ABB1 BETWEEN PARTS

RH SYMMETRICAL

VIEW LOOKING AFT

LH SHOWN

A A

F

W

D

C

(55)

01

(56) 56

A A

FR44

INBOARD

OUTBOARD

D_SB_536177_5_GAAA_02_01

Figure A-FGAAA - Sheet 02

Replacement of the Frame foot FR44, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 579

5

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

SERVICE BULLETIN

**CONF 003

D

RH SYMMETRICAL

VIEW LOOKING AFT

LH SHOWN

FR44

STGR37

B

B

H200

H201

H202

H195

H196

H197

H198

H199

H180 H181

H183 H182

H189

H190

H184

H186

H188

H187

H185

H194

H191

H192

H193

C C

C

C

B B

STGR36

02 PROTECT THE CUTÜOUT AREA WITH MAT No 04CMA2 AND MAT No 04EAC203

HEAD ON THE VISIBLE SIDE

USE EXISTING HOLES IN STRINGERS FOR THE INSTALLATION OF STIFFENERS

NOTE:

HEAD ON THE HIDDEN SIDE F

FASTENERS NOT AFFECTED

N

WET INSTALL THE FASTENERS WITH MAT No 06AAA1 EXCEPT FOR HOLES H203 AND H204 01PROTECT THE FASTENERS HEAD AND NUTS WITH MAT No 06ABA1DO SEALANT BEAD AROUND PARTS WITH MAT No 06ABB1APPLY MAT No 06ABB1 BETWEEN PARTS

HOLE

SYMBOL ITEM PN DESCRIPTION

HOLE DIAMETER

MIN MAX

(1)

(2) ASNA2529Ü3

 EN6115V3A6

NUT

SCREW 10

9

5.552 mm

(0.218 in)

5.512 mm

(0.217 in)

(1)

(2) ASNA2529Ü3

EN6115V3A7

NUT

SCREW 8

9

(1)

(2) ASNA2529Ü3

EN6115V3A3

NUT

SCREW 36

9

(3)

(4) ASNA2529Ü3

EN6115V3A7

NUT

SCREW 8

9

(3)

(4) ASNA2529Ü3

EN6115V3A6

NUT

SCREW 10

9

(5) ASNA2050DXJ4020 RIVET 19 4.170 mm (0.164 in) 4.060 mm (0.160 in)

NNNN

F

N

5.552 mm

(0.218 in)

5.512 mm

(0.217 in)

5.552 mm

(0.218 in)

5.512 mm

(0.217 in)

5.552 mm

(0.218 in)

5.512 mm

(0.217 in)

5.552 mm

(0.218 in)

5.512 mm

(0.217 in)

01

01 01

E

CUTÜOUT 02

LH

RH

106107

(106)(107)

(58)(57)

LH

RH

STGR36

FR44

03 H222

H221

FR44

(75)(74)

(73)

RH

LH

LH

RH

106107

(106)(107)

OUTBOARD

INBOARD

04 REWORK THE SURFACES WITH MAXIMUM OF THE 0.5 mm (0.020 in) DURING THE INSTALLATION OF THE NEW FRAME FOOT

04

04

04 D

D

D

D

D_SB_536177_5_GAAA_03_01

Figure A-FGAAA - Sheet 03

Replacement of the Frame foot FR44, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177REVISION No.: 00 - May 20/15 Page: 580

5

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

SERVICE BULLETIN

**CONF 003

FWD E 01

NOTE:

HEAD ON THE VISIBLE SIDE N

01 WET INSTALL THE FASTENERS WITH MAT No 06AAA1 EXCEPT FOR HOLES H203 AND H204

PROTECT THE FASTENERS HEAD AND NUTS WITH MAT No 06ABA1

DO SEALANT BEAD AROUND PARTS WITH MAT No 06ABB1

APPLY MAT No 06ABB1 BETWEEN PARTS

HOLE

SYMBOL ITEM PN DESCRIPTION

HOLE DIAMETER

MIN MAX

(3)

(4) ASNA2529Ü6

 EN6114V6X14

NUT

26 SCREW

12

9.925 mm

(0.391 in)

9.886 mm

(0.389 in)

(3)

(4) NAS1726Ü5E

ASNA2001V5Ü8Y

NUT

13 SCREW

14

8.732 mm

(0.344 in)

8.692 mm

(0.342 in)

(3)

(4) ASNA2529Ü5

 EN6114V5Y8

NUT

15 SCREW

16

N

N

N

8.732 mm

(0.344 in)

8.692 mm

(0.342 in)

H207 H208

H205 H206

H203 H204

TYPICAL SECTION

FRAME FOOT

C C

05 05

ELECTRICAL BONDING

05 SPOTFACES TO BE REALIZED DURING INSTALLATION AFTER DRILLING OF PARTS TO DIAMETER

27 mm (1.063 in) FOR OLD FASTENERS DIAMETER 9.52 mm (0.375 in) AND TO DIAMETER 29 mm (1.142 in)

FOR OLD FASTENERS DIAMETER 11.1 mm (0.437 in)

D_SB_536177_5_GAAA_04_01

Figure A-FGAAA - Sheet 04

Replacement of the Frame foot FR44, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 581

5

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

SERVICE BULLETIN

**CONF 003

NOTE:

HEAD ON THE VISIBLE SIDE N

01 WET INSTALL THE FASTENERS WITH MAT No 06AAA1 EXCEPT FOR HOLES H203 AND H204

PROTECT THE FASTENERS HEAD AND NUTS WITH MAT No 06ABA1

DO SEALANT BEAD AROUND PARTS WITH MAT No 06ABB1

APPLY MAT No 06ABB1 BETWEEN PARTS

HOLE

SYMBOL ITEM PN DESCRIPTION

HOLE DIAMETER

MIN MAX

(3)

(4) ASNA2529Ü3

 EN6115V3A5

NUT

17 SCREW

9

5.552 mm

(0.218 in)

5.512 mm

(0.217 in)

(3)

(4) ASNA2529Ü3

EN6115V3A7

NUT

8 SCREW

9

(3)

(4) ASNA2529Ü3

 EN6115V3A4

NUT

18 SCREW

9

N

N

N

5.552 mm

(0.218 in)

5.512 mm

(0.217 in)

5.552 mm

(0.218 in)

5.512 mm

(0.217 in)

FASTENERS NOT AFFECTED

RH SYMMETRICAL

VIEW LOOKING AFT

LH SHOWN

FR44

F

STGR38

STGR37

H216

H215

H214

H213

H212

H211

H210

H209

G

01

FWD

G 01

(74)

(75)

LH

RH

H220

H219

H218

H217

FR44

OUTBOARD

INBOARD

D_SB_536177_5_GAAA_05_00

Figure A-FGAAA - Sheet 05

Replacement of the Frame foot FR44, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 582

5

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

SERVICE BULLETIN

**CONF 002

F D

F

D

C

C

FR44

FR44

A

B

B

Z140

A

FR40

FR47

D_SB_536177_5_GAAB_01_00

Figure A-FGAAB - Sheet 01

Replacement of the Frame foot FR44, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 583

5

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

SERVICE BULLETIN

**CONF 002

A A

F

W

D

NOTE:

01 WET INSTALL THE FASTENERS WITH MAT No 06AAA1 EXCEPT FOR HOLES H203 AND H204

PROTECT THE FASTENERS HEAD AND NUTS WITH MAT No 06ABA1

DO SEALANT BEAD AROUND PARTS WITH MAT No 06ABB1

APPLY MAT No 06ABB1 BETWEEN PARTS

01

(55)

(56) 56 RH SYMMETRICAL

VIEW LOOKING AFT

LH SHOWN

C

A A

FR44

INBOARD

OUTBOARD

D_SB_536177_5_GAAB_02_01

Figure A-FGAAB - Sheet 02

Replacement of the Frame foot FR44, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 584

5

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

SERVICE BULLETIN

**CONF 002

D

RH SYMMETRICAL

VIEW LOOKING AFT

LH SHOWN

FR44

STGR37

B

B

H200

H201

H202

H195

H196

H197

H198

H199

H180 H181

H183 H182

H189

H190

H184

H186

H188

H187

H185

H194

H191

H192

H193

C C

C

C

B B

STGR36

02 PROTECT THE CUTÜOUT AREA WITH MAT No 04CMA2 AND MAT No 04EAC203

HEAD ON THE VISIBLE SIDE

USE EXISTING HOLES IN STRINGERS FOR THE INSTALLATION OF STIFFENERS

NOTE:

HEAD ON THE HIDDEN SIDE F

FASTENERS NOT AFFECTED

N

WET INSTALL THE FASTENERS WITH MAT No 06AAA1 EXCEPT FOR HOLES H203 AND H204 01PROTECT THE FASTENERS HEAD AND NUTS WITH MAT No 06ABA1DO SEALANT BEAD AROUND PARTS WITH MAT No 06ABB1APPLY MAT No 06ABB1 BETWEEN PARTS

HOLE

SYMBOL ITEM PN DESCRIPTION

HOLE DIAMETER

MIN MAX

(1)

(2) ASNA2529Ü3

 EN6115V3A6

NUT

SCREW 10

9

5.552 mm

(0.218 in)

5.512 mm

(0.217 in)

(1)

(2) ASNA2529Ü3

EN6115V3A7

NUT

SCREW 8

9

(1)

(2) ASNA2529Ü3

EN6115V3A3

NUT

SCREW 36

9

(3)

(4) ASNA2529Ü3

EN6115V3A7

NUT

SCREW 8

9

(3)

(4) ASNA2529Ü3

EN6115V3A6

NUT

SCREW 10

9

(5) ASNA2050DXJ4020 RIVET 19 4.170 mm (0.164 in) 4.060 mm (0.160 in)

NNNN

N

5.552 mm

(0.218 in)

5.512 mm

(0.217 in)

5.552 mm

(0.218 in)

5.512 mm

(0.217 in)

5.552 mm

(0.218 in)

5.512 mm

(0.217 in)

5.552 mm

(0.218 in)

5.512 mm

(0.217 in)

01

01 01

E

CUTÜOUT 02

LH

RH

106107

(106)(107)

(58)(57)

LH

RH

STGR36

FR44

03 H222

H221

FR44

(75)(74)

(73)

RH

LH

LH

RH

106107

(106)(107)

OUTBOARD

INBOARD

04 REWORK THE SURFACES WITH MAXIMUM OF THE 0.5 mm (0.020 in) DURING THE INSTALLATION OF THE NEW FRAME FOOT

04

04

04 D

D

D

D

F

D_SB_536177_5_GAAB_03_01

Figure A-FGAAB - Sheet 03

Replacement of the Frame foot FR44, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177REVISION No.: 00 - May 20/15 Page: 585

5

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

SERVICE BULLETIN

**CONF 002

NOTE:

HEAD ON THE VISIBLE SIDE N

01 WET INSTALL THE FASTENERS WITH MAT No 06AAA1 EXCEPT FOR HOLES H203 AND H204

PROTECT THE FASTENERS HEAD AND NUTS WITH MAT No 06ABA1

DO SEALANT BEAD AROUND PARTS WITH MAT No 06ABB1

APPLY MAT No 06ABB1 BETWEEN PARTS

HOLE

SYMBOL ITEM PN DESCRIPTION

HOLE DIAMETER

MIN MAX

(1)

(2) ASNA2529Ü6

 EN6114V6Y14

NUT

11 SCREW

12

10.321 mm

(0.406 in)

10.282 mm

(0.405 in)

(3)

(4) NAS1726Ü5E

ASNA2001V5Ü8Y

NUT

13 SCREW

14

8.732 mm

(0.344 in)

8.692 mm

(0.342 in)

(1)

(2) ASNA2529Ü5

 EN6114V5Y8

NUT

15 SCREW

16

N

8.732 mm

(0.344 in)

8.692 mm

(0.342 in)

N

N

FWD E 01

H207 H208

H205 H206

H203 H204

ELECTRICAL BONDING

TYPICAL SECTION

FRAME FOOT

C C

05 05

05 SPOTFACES TO BE REALIZED DURING INSTALLATION AFTER DRILLING OF PARTS TO DIAMETER

27 mm (1.063 in) FOR OLD FASTENERS DIAMETER 9.52 mm (0.375 in) AND TO DIAMETER 29 mm (1.142 in)

FOR OLD FASTENERS DIAMETER 11.1 mm (0.437 in) D_SB_536177_5_GAAB_04_01

Figure A-FGAAB - Sheet 04

Replacement of the Frame foot FR44, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 586

5

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

SERVICE BULLETIN

**CONF 002

NOTE:

HEAD ON THE VISIBLE SIDE N

01 WET INSTALL THE FASTENERS WITH MAT No 06AAA1 EXCEPT FOR HOLES H203 AND H204

PROTECT THE FASTENERS HEAD AND NUTS WITH MAT No 06ABA1

DO SEALANT BEAD AROUND PARTS WITH MAT No 06ABB1

APPLY MAT No 06ABB1 BETWEEN PARTS

HOLE

SYMBOL ITEM PN DESCRIPTION

HOLE DIAMETER

MIN MAX

(1)

(2) ASNA2529Ü3

 EN6115V3A7

NUT

8 SCREW

9

5.552 mm

(0.218 in)

5.512 mm

(0.217 in)

(1)

(2) ASNA2529Ü3

EN6115V3A5

NUT

17 SCREW

9

(1)

(2) ASNA2529Ü3

 EN6115V3A4

NUT

18 SCREW

9

5.552 mm

(0.218 in)

5.512 mm

(0.217 in)

5.552 mm

(0.218 in)

5.512 mm

(0.217 in)

N

N

N

FASTENERS NOT AFFECTED

RH SYMMETRICAL

VIEW LOOKING AFT

LH SHOWN

FR44

F

STGR38

STGR37

H216

H215

H214

H213

H212

H211

H210

H209

G

01

FWD

G 01

(74)

(75)

LH

RH

H220

H219

H218

H217

FR44

OUTBOARD

INBOARD

D_SB_536177_5_GAAB_05_00

Figure A-FGAAB - Sheet 05

Replacement of the Frame foot FR44, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 587

5

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

SERVICE BULLETIN

**CONF 001

F D

F

D

C

C

FR44

FR44

A

B

B

Z140

A

FR40

FR47

D_SB_536177_5_GAAC_01_00

Figure A-FGAAC - Sheet 01

Replacement of the Frame foot FR44, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 588

5

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

SERVICE BULLETIN

**CONF 001

NOTE:

01 WET INSTALL THE FASTENERS WITH MAT No 06AAA1 EXCEPT FOR HOLES H203 AND H204

PROTECT THE FASTENERS HEAD AND NUTS WITH MAT No 06ABA1

DO SEALANT BEAD AROUND PARTS WITH MAT No 06ABB1

APPLY MAT No 06ABB1 BETWEEN PARTS

RH SYMMETRICAL

VIEW LOOKING AFT

LH SHOWN

A A

F

W

D

C

(55)

01

(56) 56

A A

FR44

INBOARD

OUTBOARD

D_SB_536177_5_GAAC_02_01

Figure A-FGAAC - Sheet 02

Replacement of the Frame foot FR44, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 589

5

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

SERVICE BULLETIN

**CONF 001

D

RH SYMMETRICAL

VIEW LOOKING AFT

LH SHOWN

FASTENERS NOT AFFECTED

NOTE:

FR44

B B

01

01

WET INSTALL THE FASTENERS WITH MAT No 06AAA1 EXCEPT FOR HOLES H203 AND H204 01PROTECT THE FASTENERS HEAD AND NUTS WITH MAT No 06ABA1DO SEALANT BEAD AROUND PARTS WITH MAT No 06ABB1APPLY MAT No 06ABB1 BETWEEN PARTS

USE EXISTING HOLES IN STRINGERS FOR THE 02

INSTALLATION OF STIFFENERS

LH

RH

106107

(106)(107)

(58)(57)

LH

RH

STGR36

FR44

02 H222

H221

STGR37

B

B

H200

H201

H202

H195

H196

H197

H198

H199

H180 H181

H183 H182

H189

H190

H184

H186

H188

H187

H185

H194

H192

H193

STGR36

E

LH

RH

106

107

(106)(107)

OUTBOARD

INBOARD

03

03

03

H191

03 REWORK THE SURFACES WITH MAXIMUM OF THE 0.5 mm (0.020 in) DURING THE INSTALLATION OF THE NEW FRAME FOOT

C

C

C

C

D_SB_536177_5_GAAC_03_01

Figure A-FGAAC - Sheet 03

Replacement of the Frame foot FR44, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177REVISION No.: 00 - May 20/15 Page: 590

5

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

SERVICE BULLETIN

**CONF 001

NOTE:

HEAD ON THE VISIBLE SIDE N

HOLE

SYMBOL ITEM PN DESCRIPTION

HOLE DIAMETER

MIN MAX

ASNA2529Ü3

EN6115V3X6 (5)

OR

(6)

(7)

NUT

SCREW

ASNA2529Ü3

 EN6115V3X6

NUT

SCREW

5.152 mm

(0.203 in)

5.113 mm

(0.201 in)

25

9

25

9

N

5.152 mm

(0.203 in)

5.113 mm

(0.201 in)

ASNA2529Ü3

EN6115V3X7 (5)

OR

(6)

(7)

NUT

SCREW

ASNA2529Ü3

 EN6115V3X7

NUT

SCREW

5.152 mm

(0.203 in)

5.113 mm

(0.201 in)

24

9

24

9

5.152 mm

(0.203 in)

5.113 mm

(0.201 in)

N

ASNA2529Ü3

EN6115V3X5 (5)

OR

(6)

(7)

NUT

SCREW

ASNA2529Ü3

 EN6115V3X5

NUT

SCREW

5.152 mm

(0.203 in)

5.113 mm

(0.201 in)

23

9

23

9

5.152 mm

(0.203 in)

5.113 mm

(0.201 in)

N

(3)

(4) ASNA2529Ü3

 EN6115V3X7

NUT

24 SCREW

9

5.152 mm

(0.203 in)

5.113 mm

(0.201 in)

(3)

(4) ASNA2529Ü3

 EN6115V3X6

NUT

25 SCREW

9

5.152 mm

(0.203 in)

5.113 mm

(0.201 in)

(19) 19 ASNA2050DXJ4020 RIVET 4.170 mm

(0.164 in)

4.060 mm

(0.160 in)

N

F

N

HEAD ON THE HIDDEN SIDE F

D_SB_536177_5_GAAC_04_00

Figure A-FGAAC - Sheet 04

Replacement of the Frame foot FR44, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 591

5

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

SERVICE BULLETIN

**CONF 001

FWD E 01

NOTE:

HEAD ON THE VISIBLE SIDE N

01 WET INSTALL THE FASTENERS WITH MAT No 06AAA1 EXCEPT FOR HOLES H203 AND H204

PROTECT THE FASTENERS HEAD AND NUTS WITH MAT No 06ABA1

DO SEALANT BEAD AROUND PARTS WITH MAT No 06ABB1

APPLY MAT No 06ABB1 BETWEEN PARTS

HOLE

SYMBOL ITEM PN DESCRIPTION

HOLE DIAMETER

MIN MAX

(3)

(4) ASNA2529Ü6

 EN6114V6X14

NUT

26 SCREW

12

9.925 mm

(0.391 in)

9.886 mm

N (0.389 in)

(3)

(4) NAS1726Ü5E

ASNA2001V5Ü8X

NUT

27 SCREW

14

8.335 mm

(0.328 in)

8.296 mm

(0.327 in)

(3)

(4) ASNA2529Ü5

 EN6114V5X8

NUT

28 SCREW

16

N

N

8.335 mm

(0.328 in)

8.296 mm

(0.327 in)

H207 H208

H205 H206

H203 H204

04 SPOTFACES TO BE REALIZED DURING INSTALLATION AFTER DRILLING OF PARTS TO DIAMETER

27 mm (1.063 in) FOR OLD FASTENERS DIAMETER 9.52 mm (0.375 in) AND TO DIAMETER 29 mm (1.142 in)

FOR OLD FASTENERS DIAMETER 11.1 mm (0.437 in)

ELECTRICAL BONDING

TYPICAL SECTION

FRAME FOOT

C C

04 04

D_SB_536177_5_GAAC_05_01

Figure A-FGAAC - Sheet 05

Replacement of the Frame foot FR44, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 592

5

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

SERVICE BULLETIN

**CONF 001

NOTE:

HEAD ON THE VISIBLE SIDE N

01 WET INSTALL THE FASTENERS WITH MAT No 06AAA1 EXCEPT FOR HOLES H203 AND H204

PROTECT THE FASTENERS HEAD AND NUTS WITH MAT No 06ABA1

DO SEALANT BEAD AROUND PARTS WITH MAT No 06ABB1

APPLY MAT No 06ABB1 BETWEEN PARTS

HOLE

SYMBOL ITEM PN DESCRIPTION

HOLE DIAMETER

MIN MAX

(3)

(4) ASNA2529Ü3

 EN6115V3X7

NUT

24 SCREW

9

5.152 mm

(0.203 in)

5.113 mm

(0.201 in)

(3)

(4) ASNA2529Ü3

EN6115V3X5

NUT

23 SCREW

9

(3)

(4) ASNA2529Ü3

 EN6115V3X4

NUT

29 SCREW

9

N

N

N

5.152 mm

(0.203 in)

5.113 mm

(0.201 in)

5.152 mm

(0.203 in)

5.113 mm

(0.201 in)

FASTENERS NOT AFFECTED

RH SYMMETRICAL

VIEW LOOKING AFT

LH SHOWN

FR44

F

FWD

STGR38

STGR37

H216

H215

H214

H213

H212

H211

H210

H209

G

01 G 01

(74)

(75)

LH

RH

H220

H219

H218

H217

FR44

OUTBOARD

INBOARD

D_SB_536177_5_GAAC_06_00

Figure A-FGAAC - Sheet 06

Replacement of the Frame foot FR44, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 593

5

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

SERVICE BULLETIN

**CONF 003

FR40

A

B

FR47

FR45

B

Z140

A

C

D

F

C

D

F

FR45

D_SB_536177_5_JAAA_01_00

Figure A-FJAAA - Sheet 01

Replacement of the Frame foot FR45, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 594

5

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

SERVICE BULLETIN

**CONF 003

RH SYMMETRICAL

VIEW LOOKING AFT

LH SHOWN

A A

F

W

D

C

(55)

01 WET INSTALL THE FASTENERS WITH MAT. No 06AAA1 EXCEPT FOR HOLES H269 AND H270

PROTECT THE FASTENERS HEAD AND NUTS WITH MAT. No 06ABA1

DO SEALANT BEAD AROUND PARTS WITH MAT. No 06ABB1

APPLY MAT. No 06ABB1 BETWEEN PARTS

01

NOTE:

A A

FR45

INBOARD

OUTBOARD

OR (76) 76

(56) 56

D_SB_536177_5_JAAA_02_01

Figure A-FJAAA - Sheet 02

Replacement of the Frame foot FR45, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 595

5

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

SERVICE BULLETIN

**CONF 003

H230

H245

H252

H251

H250

H249

H248

H264 H259 H261 H263

H262

H260

H231

H258

H244

H242

H243

H241

H247

H246

H240

H239 H238

H237

H234

H257

H232

H235

(77)

STGR37

STGR36

D

RH SYMMETRICAL

VIEW LOOKING AFT

LH SHOWN

FR45

H236

H266

LH

RH

(72)

(71)

FASTENERS NOT AFFECTED B B NOTE:

01 WET INSTALL THE FASTENERS WITH MAT. No 06AAA1 EXCEPT FOR HOLES H269 AND H270

PROTECT THE FASTENERS HEAD AND NUTS WITH MAT. No 06ABA1

DO SEALANT BEAD AROUND PARTS WITH MAT. No 06ABB1

APPLY MAT. No 06ABB1 BETWEEN PARTS

02 PROTECT THE CUTÜOUT AREA WITH MAT. No 04CMA2 AND MAT. No 0EAC2

01

03 USE EXISTING HOLES IN STRINGERS FOR THE INSTALLATION OF STIFFENERS

C

C

LH

RH

(108) 108

(109) 109

E

01

H233

CUTÜOUT

02

H265

H253

H254

LH

RH

(58)

(57)

LH

RH

(108) 108

(109) 109

03

H255

H256

STGR36

FR45

INBOARD

OUTBOARD

E

E E

E

B

B

06 REWORK THE SURFACES WITH MAXIMUM OF THE 0.5 mm (0.020 in)

DURING THE INSTALLATION OF THE NEW FRAME FOOT

06

06

D

D

D_SB_536177_5_JAAA_03_01

Figure A-FJAAA - Sheet 03

Replacement of the Frame foot FR45, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 596

5

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

SERVICE BULLETIN

**CONF 003

5.512 mm

(0.217 in)

5.512 mm

(0.217 in)

5.552 mm

(0.218 in)

5.552 mm

(0.218 in) (5)

(94)

NUT

SCREW

NUT

ASNA2529Ü3

EN6115V3A5

ASNA2529Ü3

HOLE

SYMBOL ITEM PART NUMBER DESCRIPTION

HOLE DIAMETER

MIN MAX

(93) EN6115V3A5 SCREW

HEAD ON THE VISIBLE SIDE

NOTE:

9

17

9

17

5.512 mm

(0.217 in)

5.512 mm

(0.217 in)

5.552 mm

(0.218 in)

5.552 mm

(0.218 in) (5)

(94)

NUT

SCREW

NUT

ASNA2529Ü3

EN6114V3A6

ASNA2529Ü3

(93) EN6114V3A6 SCREW

9

42

9

42

5.512 mm

(0.217 in)

5.512 mm

(0.217 in)

5.552 mm

(0.218 in)

5.552 mm

(0.218 in) (5)

(94)

NUT

SCREW

NUT

ASNA2529Ü3

EN6115V3A6

ASNA2529Ü3

(93) EN6115V3A6 SCREW

9

10

9

10

5.512 mm

(0.217 in)

5.552 mm

(2) ASNA2529Ü3 NUT (0.218 in)

(1) EN6115V3A9 SCREW

9

33

4.060 mm

(0.160 in)

4.170 mm

(0.164 in) (19) 19 ASNA2050DXJ4020 RIVET

5.512 mm

(0.217 in)

5.552 mm

(4) ASNA2529Ü3 NUT (0.218 in)

(3) EN6115V3A6 SCREW

9

10

OR

OR

OR

HEAD ON THE HIDDEN SIDE F

N

5.512 mm

(0.217 in)

5.552 mm

(4) ASNA2529Ü3 NUT (0.218 in)

(3) EN6115V3A8 SCREW

9

32

5.512 mm

(0.217 in)

5.552 mm

(4) ASNA2529Ü3 NUT (0.218 in)

(3) EN6115V3A9 SCREW

9

33

5.512 mm

(0.217 in)

5.512 mm

(0.217 in)

5.552 mm

(0.218 in)

5.552 mm

(0.218 in) (5)

(94)

NUT

SCREW

NUT

ASNA2529Ü3

EN6115V3A7

ASNA2529Ü3

(93) EN6115V3A7 SCREW

9

8

9

8

OR

5.512 mm

(0.217 in)

5.552 mm

(2) ASNA2529Ü3 NUT (0.218 in)

(1) EN6115V3A10 SCREW

9

43

5.512 mm

(0.217 in)

5.552 mm

(2) ASNA2529Ü3 NUT (0.218 in)

(1) EN6115V3A11 SCREW

9

44

N

N

N

N

F

F

F

N

F

N

N

D_SB_536177_5_JAAA_04_00

Figure A-FJAAA - Sheet 04

Replacement of the Frame foot FR45, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 597

5

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

SERVICE BULLETIN

**CONF 003

FWD

9.886 mm

(0.389 in)

9.925 mm

NUT (0.391 in)

SCREW

ASNA2529Ü6

EN6114V6X14

HOLE

SYMBOL ITEM PART NUMBER DESCRIPTION

HOLE DIAMETER

MIN MAX

HEAD ON THE VISIBLE SIDE

NOTE:

12

26

N

10.282 mm

(0.405 in)

10.321 mm

NUT (0.406 in)

SCREW

NAS1726Ü6E

ASNA2001V6Ü8Y

46

45

4.060 mm

(0.160 in)

4.170 mm

(0.164 in) (19) 19 ASNA2050DXJ4020 RIVET

03 USE EXISTING HOLES IN STRINGERS FOR THE INSTALLATION OF STIFFENERS

01 WET INSTALL THE FASTENERS WITH MAT. No 06AAA1 EXCEPT FOR HOLES H269 AND H270

PROTECT THE FASTENERS HEAD AND NUTS WITH MAT. No 06ABA1

DO SEALANT BEAD AROUND PARTS WITH MAT. No 06ABB1

APPLY MAT. No 06ABB1 BETWEEN PARTS

(4)

(3)

(4)

(3)

E 01

(77) (78)

(58)

(57)

LH

RH

LH

RH

(108) 108

(109) 109

N

N

N

H269 H270

H271 H272

STGR37

FR45

01

03

01

STGR37

(78)

(58)

(57)

LH

RH

(77)

H268

H267

C C

D D ELECTRICAL BONDING

D_SB_536177_5_JAAA_05_01

Figure A-FJAAA - Sheet 05

Replacement of the Frame foot FR45, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 598

5

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

SERVICE BULLETIN

**CONF 003

IF INSTALLED, REMOVE THE BRACKET, LH SIDE ONLY 04

WET INSTALL THE FASTENERS WITH MAT. No 06AAA1 EXCEPT FOR HOLES H269 AND H270 01

PROTECT THE FASTENERS HEAD AND NUTS WITH MAT. No 06ABA1

DO SEALANT BEAD AROUND PARTS WITH MAT. No 06ABB1

APPLY MAT. No 06ABB1 BETWEEN PARTS

FWD

STGR39

STGR38

H281

H280

H279

H278

H277

H276

H275

H274

H273

FR45

RH SYMMETRICAL

VIEW LOOKING AFT

LH SHOWN

04 (79)

F G

G

FASTENERS NOT AFFECTED

NOTE:

5.512 mm

(0.217 in)

5.552 mm

(0.218 in)

NUT

SCREW

ASNA2529Ü3

EN6115V3A6

HOLE

SYMBOL ITEM PART NUMBER DESCRIPTION HOLE DIAMETER MIN MAX

HEAD ON THE VISIBLE SIDE

9

10

N

SCREW 17

NUT

EN6115V3A5

9

5.512 mm

(0.217 in)

5.552 mm

(0.218 in)

(3)(4)(3)(4)

NUT

SCREW

ASNA2529Ü3

EN6115V3A9 33

9

(3)(4)

HEAD ON THE HIDDEN SIDE F

5.512 mm

(0.217 in)

5.552 mm

(0.218 in) NUT

SCREW

ASNA2529Ü3

EN6115V3A7 8

9

(3)(4)

REMARKS

5.512 mm

(0.217 in)

5.552 mm

(0.218 in) NUT

SCREW

ASNA2529Ü3

EN6115V3A8 32

9

(3)(4)

ASNA2529Ü3

OR

5.512 mm

(0.217 in)

5.552 mm

(0.218 in) NUT

SCREW

ASNA2529Ü3

EN6115V3A5

9

17 (3)

(4)

N 05

ÜÜÜÜ

01 01

FFF

N

05 AND ARE FOR LH SIDE AND ITEMS AND ARE FOR RH SIDE ITEMS 9 10 9 17

(72)(71)

RH

LH

H282

H283

H284

H285

FR45

OUTBOARD

INBOARD

07 07

FRAME FOOT

TYPICAL SECTION

SPOTFACES TO BE REALIZED DURING INSTALLATION AFTER DRILLING OF PARTS TO DIAMETER 27 mm 07

(1.063 in) FOR OLD FASTENERS DIAMETER 9.52 mm (0.375 in) AND TO DIAMETER 29 mm (1.142 in)

 FOR OLD FASTENERS DIAMETER 11.1 mm (0.437 in)

E E

D_SB_536177_5_JAAA_06_01

Figure A-FJAAA - Sheet 06

Replacement of the Frame foot FR45, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177REVISION No.: 00 - May 20/15 Page: 599

5

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

SERVICE BULLETIN

**CONF 002

FR40

A

B

FR47

FR45

B

Z140

A

C

D

F

C

D

F

FR45

D_SB_536177_5_JAAB_01_00

Figure A-FJAAB - Sheet 01

Replacement of the Frame foot FR45, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 600

5

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

SERVICE BULLETIN

**CONF 002

RH SYMMETRICAL

VIEW LOOKING AFT

LH SHOWN

A A

F

W

D

C

(55)

01 WET INSTALL THE FASTENERS WITH MAT. No 06AAA1 EXCEPT FOR HOLES H269 AND H270

PROTECT THE FASTENERS HEAD AND NUTS WITH MAT. No 06ABA1

DO SEALANT BEAD AROUND PARTS WITH MAT. No 06ABB1

APPLY MAT. No 06ABB1 BETWEEN PARTS

01

NOTE:

A A

FR45

INBOARD

OUTBOARD

OR (76) 76

(56) 56

D_SB_536177_5_JAAB_02_01

Figure A-FJAAB - Sheet 02

Replacement of the Frame foot FR45, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 601

5

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

SERVICE BULLETIN

**CONF 002

H230

H245

H252

H251

H250

H249

H248

H264 H259 H261 H263

H262

H260

H231

H258

H244

H242

H243

H241

H247

H246

H240

H239 H238

H237

H234

H257

H232

H235

STGR37

STGR36

D

RH SYMMETRICAL

VIEW LOOKING AFT

LH SHOWN

FR45

H236

H266

LH

RH

(72)

(71)

FASTENERS NOT AFFECTED B B NOTE:

01 WET INSTALL THE FASTENERS WITH MAT. No 06AAA1 EXCEPT FOR HOLES H269 AND H270

PROTECT THE FASTENERS HEAD AND NUTS WITH MAT. No 06ABA1

DO SEALANT BEAD AROUND PARTS WITH MAT. No 06ABB1

APPLY MAT. No 06ABB1 BETWEEN PARTS

02 PROTECT THE CUTÜOUT AREA WITH MAT. No 04CMA2 AND MAT. No 0EAC2

01

03 USE EXISTING HOLES IN STRINGERS FOR THE INSTALLATION OF STIFFENERS

C

C

LH

RH

(108) 108

(109) 109

E

01

H233

CUTÜOUT

02

H265

H253

H254

LH

RH

(58)

(57)

LH

RH

(108) 108

(109) 109

03

H255

H256

STGR36

FR45

INBOARD

OUTBOARD

E

E E

E

B

B

06 REWORK THE SURFACES WITH MAXIMUM OF THE 0.5 mm (0.020 in)

DURING THE INSTALLATION OF THE NEW FRAME FOOT

06

06

D

D

D_SB_536177_5_JAAB_03_01

Figure A-FJAAB - Sheet 03

Replacement of the Frame foot FR45, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 602

5

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

SERVICE BULLETIN

**CONF 002

5.512 mm

(0.217 in)

5.512 mm

(0.217 in)

5.552 mm

(0.218 in)

5.552 mm

(0.218 in) (5)

(94)

NUT

SCREW

NUT

ASNA2529Ü3

EN6115V3A5

ASNA2529Ü3

HOLE

SYMBOL ITEM PART NUMBER DESCRIPTION

HOLE DIAMETER

MIN MAX

(93) EN6115V3A5 SCREW

HEAD ON THE VISIBLE SIDE

NOTE:

9

17

9

17

5.512 mm

(0.217 in)

5.552 mm

(2) ASNA2529Ü3 NUT (0.218 in)

(1) EN6114V3A6 SCREW

9

42

5.512 mm

(0.217 in)

5.552 mm

(2) ASNA2529Ü3 NUT (0.218 in)

(1) EN6115V3A6 SCREW

9

10

5.512 mm

(0.217 in)

5.552 mm

(2) ASNA2529Ü3 NUT (0.218 in)

(1) EN6115V3A9 SCREW

9

33

4.060 mm

(0.160 in)

4.170 mm

(0.164 in) (19) 19 ASNA2050DXJ4020 RIVET

5.512 mm

(0.217 in)

5.552 mm

(2) ASNA2529Ü3 NUT (0.218 in)

(1) EN6115V3A6 SCREW

9

10

OR

HEAD ON THE HIDDEN SIDE F

N

5.512 mm

(0.217 in)

5.552 mm

(2) ASNA2529Ü3 NUT (0.218 in)

(1) EN6115V3A8 SCREW

9

32

5.512 mm

(0.217 in)

5.552 mm

(2) ASNA2529Ü3 NUT (0.218 in)

(1) EN6115V3A9 SCREW

9

33

5.512 mm

(0.217 in)

5.552 mm

(2) ASNA2529Ü3 NUT (0.218 in)

(1) EN6115V3A7 SCREW

9

8

5.512 mm

(0.217 in)

5.552 mm

(2) ASNA2529Ü3 NUT (0.218 in)

(1) EN6115V3A10 SCREW

9

43

5.512 mm

(0.217 in)

5.552 mm

(2) ASNA2529Ü3 NUT (0.218 in)

(1) EN6115V3A11 SCREW

9

44

N

N

F

N

N

N

F

F

F

N

N

D_SB_536177_5_JAAB_04_00

Figure A-FJAAB - Sheet 04

Replacement of the Frame foot FR45, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 603

5

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

SERVICE BULLETIN

**CONF 002

10.282 mm

(0.405 in)

10.321 mm

NUT (0.406 in)

SCREW

ASNA2529Ü6

EN6114V6Y14

HOLE

SYMBOL ITEM PART NUMBER DESCRIPTION

HOLE DIAMETER

MIN MAX

HEAD ON THE VISIBLE SIDE

NOTE:

12

11

N

10.282 mm

(0.405 in)

10.321 mm

NUT (0.406 in)

SCREW

NAS1726Ü6E

ASNA2001V6Ü8Y

46

45

4.060 mm

(0.160 in)

4.170 mm

(0.164 in) (19) 19 ASNA2050DXJ4020 RIVET

03 USE EXISTING HOLES IN STRINGERS FOR THE INSTALLATION OF STIFFENERS

01 WET INSTALL THE FASTENERS WITH MAT. No 06AAA1 EXCEPT FOR HOLES H269 AND H270

PROTECT THE FASTENERS HEAD AND NUTS WITH MAT. No 06ABA1

DO SEALANT BEAD AROUND PARTS WITH MAT. No 06ABB1

APPLY MAT. No 06ABB1 BETWEEN PARTS

(2)

(1)

(4)

(3)

N

N

N

FWD

E 01

(77) (78)

(58)

(57)

LH

RH

LH

RH

(108) 108

(109) 109

H269 H270

H271 H272

STGR37

FR45

01

03

01

STGR37

(78)

(58)

(57)

LH

RH

(77)

H268

H267

C C

D D ELECTRICAL BONDING

D_SB_536177_5_JAAB_05_01

Figure A-FJAAB - Sheet 05

Replacement of the Frame foot FR45, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 604

5

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

SERVICE BULLETIN

**CONF 002

IF INSTALLED, REMOVE THE BRACKET, LH SIDE ONLY 04

WET INSTALL THE FASTENERS WITH MAT. No 06AAA1 EXCEPT FOR HOLES H269 AND H270 01

PROTECT THE FASTENERS HEAD AND NUTS WITH MAT. No 06ABA1

DO SEALANT BEAD AROUND PARTS WITH MAT .No 06ABB1

APPLY MAT. No 06ABB1 BETWEEN PARTS

STGR39

STGR38

H281

H280

H279

H278

H277

H276

H275

H274

H273

FR45

RH SYMMETRICAL

VIEW LOOKING AFT

LH SHOWN

04 (79)

F

G

FASTENERS NOT AFFECTED

NOTE:

5.512 mm

(0.217 in)

5.552 mm

(0.218 in)

NUT

SCREW

ASNA2529Ü3

EN6115V3A6

HOLE

SYMBOL ITEM PART NUMBER DESCRIPTION HOLE DIAMETER MIN MAX

HEAD ON THE VISIBLE SIDE

9

10

N

SCREW 17

NUT

EN6115V3A5

9

5.512 mm

(0.217 in)

5.552 mm

(0.218 in)

(3)(4)(3)(4)

NUT

SCREW

ASNA2529Ü3

EN6115V3A9 33

9

(3)(4)

HEAD ON THE HIDDEN SIDE F

5.512 mm

(0.217 in)

5.552 mm

(0.218 in) NUT

SCREW

ASNA2529Ü3

EN6115V3A7 8

9

(3)(4)

REMARKS

5.512 mm

(0.217 in)

5.552 mm

(0.218 in) NUT

SCREW

ASNA2529Ü3

EN6115V3A8 32

9

(3)(4)

ASNA2529Ü3

OR

5.512 mm

(0.217 in)

5.552 mm

(0.218 in) NUT

SCREW

ASNA2529Ü3

EN6115V3A5

9

17 (3)

(4)

N 05

ÜÜÜÜ

01 F

FF

N

05 AND ARE FOR LH SIDE AND ITEMS AND ARE FOR RH SIDE ITEMS 9 10 9 17

FWD

G 01

(72)(71)

RH

LH

H282

H283

H284

H285

FR45

OUTBOARD

INBOARD

07 07

FRAME FOOT

TYPICAL SECTION

E E

SPOTFACES TO BE REALIZED DURING INSTALLATION AFTER DRILLING OF PARTS TO DIAMETER 27 mm 07

(1.063 in) FOR OLD FASTENERS DIAMETER 9.52 mm (0.375 in) AND TO DIAMETER 29 mm (1.142 in)

 FOR OLD FASTENERS DIAMETER 11.1 mm (0.437 in) D_SB_536177_5_JAAB_06_01

Figure A-FJAAB - Sheet 06

Replacement of the Frame foot FR45, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177REVISION No.: 00 - May 20/15 Page: 605

5

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

SERVICE BULLETIN

**CONF 001

FR40

A

B

FR47

FR45

B

Z140

A

C

D

F

C

D

F

FR45

D_SB_536177_5_JAAC_01_00

Figure A-FJAAC - Sheet 01

Replacement of the Frame foot FR45, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 606

5

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

SERVICE BULLETIN

**CONF 001

RH SYMMETRICAL

VIEW LOOKING AFT

LH SHOWN

A A

F

W

D

C

(55)

01 WET INSTALL THE FASTENERS WITH MAT. No 06AAA1 EXCEPT FOR HOLES H269 AND H270

PROTECT THE FASTENERS HEAD AND NUTS WITH MAT. No 06ABA1

DO SEALANT BEAD AROUND PARTS WITH MAT. No 06ABB1

APPLY MAT. No 06ABB1 BETWEEN PARTS

01

NOTE:

A A

FR45

INBOARD

OUTBOARD

OR (76) 76

(56) 56

D_SB_536177_5_JAAC_02_01

Figure A-FJAAC - Sheet 02

Replacement of the Frame foot FR45, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 607

5

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

SERVICE BULLETIN

**CONF 001

H230

H245

H252

H251

H250

H249

H248

H264 H259 H261 H263

H262

H260

H231

H258

H244

H242

H243

H241

H247

H246

H240

H239 H238

H237

H234

H257

H232

H235

STGR37

STGR36

D

RH SYMMETRICAL

VIEW LOOKING AFT

LH SHOWN

FR45

H236

H266

LH

RH

(72)

(71)

B B

FASTENERS NOT AFFECTED

NOTE:

01 WET INSTALL THE FASTENERS WITH MAT. No 06AAA1 EXCEPT FOR HOLES H269 AND H270

PROTECT THE FASTENERS HEAD AND NUTS WITH MAT. No 06ABA1

DO SEALANT BEAD AROUND PARTS WITH MAT. No 06ABB1

APPLY MAT. No 06ABB1 BETWEEN PARTS

01

02 USE EXISTING HOLES IN STRINGERS FOR THE INSTALLATION OF STIFFENERS

C

C

LH

RH

(108) 108

(109) 109

E

01

H233

H265

H253

H254

LH

RH

(58)

(57)

LH

RH

(108) 108

(109) 109

02

H255

H256

STGR36

FR45

INBOARD

OUTBOARD

B

B

05 REWORK THE SURFACES WITH MAXIMUM OF THE 0.5 mm (0.020 in)

DURING THE INSTALLATION OF THE NEW FRAME FOOT

05

05

D

D

D

D

D_SB_536177_5_JAAC_03_01

Figure A-FJAAC - Sheet 03

Replacement of the Frame foot FR45, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 608

5

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

SERVICE BULLETIN

**CONF 001

5.113 mm

(0.201 in)

5.113 mm

(0.201 in)

5.152 mm

(0.203 in)

5.152 mm

(0.203 in) (5)

(94)

NUT

SCREW

NUT

ASNA2529Ü3

EN6115V3X5

ASNA2529Ü3

HOLE

SYMBOL ITEM PART NUMBER DESCRIPTION

HOLE DIAMETER

MIN MAX

(93) EN6115V3X5 SCREW

HEAD ON THE VISIBLE SIDE

NOTE:

9

23

9

23

5.113 mm

(0.201 in)

5.113 mm

(0.201 in)

5.152 mm

(0.203 in)

5.152 mm

(0.203 in) (5)

(94)

NUT

SCREW

NUT

ASNA2529Ü3

EN6114V3X6

ASNA2529Ü3

(93) EN6114V3X6 SCREW

9

47

9

47

5.113 mm

(0.201 in)

5.113 mm

(0.201 in)

5.152 mm

(0.203 in)

5.152 mm

(0.203 in) (5)

(94)

NUT

SCREW

NUT

ASNA2529Ü3

EN6115V3X6

ASNA2529Ü3

(93) EN6115V3X6 SCREW

9

25

9

25

5.113 mm

(0.201 in)

5.152 mm

(4) ASNA2529Ü3 NUT (0.203 in)

(3) EN6115V3X8 SCREW

9

40

4.060 mm

(0.160 in)

4.170 mm

(0.164 in) (19) 19 ASNA2050DXJ4020 RIVET

5.113 mm

(0.201 in)

5.152 mm

(4) ASNA2529Ü3 NUT (0.203 in)

(3) EN6115V3X7 SCREW

9

24

OR

OR

OR

HEAD ON THE HIDDEN SIDE F

N

5.113 mm

(0.201 in)

5.152 mm

(4) ASNA2529Ü3 NUT (0.203 in)

(3) EN6115V3X9 SCREW

9

39

5.113 mm

(0.201 in)

5.152 mm

(4) ASNA2529Ü3 NUT (0.203 in)

(3) EN6115V3X6 SCREW

9

25

5.113 mm

(0.201 in)

5.113 mm

(0.201 in)

5.152 mm

(0.203 in)

5.152 mm

(0.203 in) (5)

(94)

NUT

SCREW

NUT

ASNA2529Ü3

EN6115V3X7

ASNA2529Ü3

(93) EN6115V3X7 SCREW

9

24

9

24

OR

N

N

N

F

F

F

F

N

N

D_SB_536177_5_JAAC_04_00

Figure A-FJAAC - Sheet 04

Replacement of the Frame foot FR45, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 609

5

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

SERVICE BULLETIN

**CONF 001

FWD

(58)

(57)

LH

RH

9.886 mm

(0.389 in)

9.925 mm

NUT (0.391 in)

SCREW

ASNA2529Ü6

EN6114V6X14

HOLE

SYMBOL ITEM PART NUMBER DESCRIPTION

HOLE DIAMETER

MIN MAX

HEAD ON THE VISIBLE SIDE

NOTE:

12

26

N

9.886 mm

(0.389 in)

9.925 mm

NUT (0.391 in)

SCREW

NAS1726Ü6E

ASNA2001V6Ü8X

46

48

4.060 mm

(0.160 in)

4.170 mm

(0.164 in) (19) 19 ASNA2050DXJ4020 RIVET

02 USE EXISTING HOLES IN STRINGERS FOR THE INSTALLATION OF STIFFENERS

01 WET INSTALL THE FASTENERS WITH MAT. No 06AAA1 EXCEPT FOR HOLES H269 AND H270

PROTECT THE FASTENERS HEAD AND NUTS WITH MAT. No 06ABA1

DO SEALANT BEAD AROUND PARTS WITH MAT. No 06ABB1

APPLY MAT. No 06ABB1 BETWEEN PARTS

N (4)

(3)

(4)

(3)

E

C C

N

01

01

LH

RH

(108) 108

(109) 109

H269 H270

H271 H272

STGR37

FR45

02

H267

H268

N

ELECTRICAL BONDING

D_SB_536177_5_JAAC_05_01

Figure A-FJAAC - Sheet 05

Replacement of the Frame foot FR45, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 610

5

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

SERVICE BULLETIN

**CONF 001

IF INSTALLED, REMOVE THE BRACKET, LH SIDE ONLY 03

WET INSTALL THE FASTENERS WITH MAT. No 06AAA1 EXCEPT FOR HOLES H269 AND H270 01

PROTECT THE FASTENERS HEAD AND NUTS WITH MAT. No 06ABA1

DO SEALANT BEAD AROUND PARTS WITH MAT. No 06ABB1

APPLY MAT. No 06ABB1 BETWEEN PARTS

04

FWD

STGR39

STGR38

H281

H280

H279

H278

H277

H276

H275

H274

H273

FR45

RH SYMMETRICAL

VIEW LOOKING AFT

LH SHOWN

03 (79)

(71)(72)

RH

LH

F G

G

FASTENERS NOT AFFECTED

NOTE:

5.113 mm

(0.201 in)

5.152 mm

(0.203 in)

NUT

SCREW

ASNA2529Ü3

EN6115V3X6

HOLE

SYMBOL ITEM PART NUMBER DESCRIPTION HOLE DIAMETER MIN MAX

HEAD ON THE VISIBLE SIDE

25

9

N

SCREW 23

NUT

EN6115V3X5

9

5.113 mm

(0.201 in)

5.152 mm

(0.203 in)

(3)

(4)(3)

(4)

NUT

SCREW

ASNA2529Ü3

EN6115V3X9 39

9

(3)

(4)

HEAD ON THE HIDDEN SIDE F

F

FF

5.113 mm

(0.201 in)

5.152 mm

(0.203 in) NUT

SCREW

ASNA2529Ü3

EN6115V3X7

9

24 (3)

(4)

REMARKS

5.113 mm

(0.201 in)

5.152 mm

(0.203 in) NUT

SCREW

ASNA2529Ü3

EN6115V3X8 40

9

(3)

(4)

ASNA2529Ü3

OR

5.113 mm

(0.201 in)

5.152 mm

(0.203 in) NUT

SCREW

ASNA2529Ü3

EN6115V3X5 23

9

(3)

(4)

NN

04

ÜÜÜÜ

01 01

AND ARE FOR LH SIDE AND ITEMS AND ARE FOR RH SIDE ITEMS 9 25 9 23

H282

H283

H284

H285

FR45

OUTBOARD

INBOARD

SPOTFACES TO BE REALIZED DURING INSTALLATION AFTER DRILLING OF PARTS TO DIAMETER 27 mm 06

(1.063 in) FOR OLD FASTENERS DIAMETER 9.52 mm (0.375 in) AND TO DIAMETER 29 mm (1.142 in)

 FOR OLD FASTENERS DIAMETER 11.1 mm (0.437 in)

06 06

FRAME FOOT

D D

TYPICAL SECTION

D_SB_536177_5_JAAC_06_01

Figure A-FJAAC - Sheet 06

Replacement of the Frame foot FR45, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177REVISION No.: 00 - May 20/15 Page: 611

5

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

SERVICE BULLETIN

**CONF 003

FR40

A

B

FR47

FR46

B

Z140

A

C

D

F

C

D

F

FR46

D_SB_536177_5_KAAA_01_00

Figure A-FKAAA - Sheet 01

Replacement of the Frame foot FR46, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 612

5

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

SERVICE BULLETIN

**CONF 003

RH SYMMETRICAL

VIEW LOOKING AFT

LH SHOWN

A A

F

W

D

C

(55)

01 WET INSTALL THE FASTENERS WITH MAT. No 06AAA1 EXCEPT FOR HOLES H332 AND H333

PROTECT THE FASTENERS HEAD AND NUTS WITH MAT. No 06ABA1

DO SEALANT BEAD AROUND PARTS WITH MAT. No 06ABB1

APPLY MAT. No 06ABB1 BETWEEN PARTS

01

NOTE:

A A

FR46

INBOARD

OUTBOARD

OR (76) 76

(56) 56

D_SB_536177_5_KAAA_02_01

Figure A-FKAAA - Sheet 02

Replacement of the Frame foot FR46, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 613

5

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

SERVICE BULLETIN

**CONF 003

B

B

STGR37

D

RH SYMMETRICAL

VIEW LOOKING AFT

LH SHOWN

FR46

C

C

(81)

H331

80

H321

H308 H307

H306

H320

H319

H304

H305

H318

H310

H309 H313

H317

H302

H303 H312

H311 H301

H300

H316 H324

H326 H329

H330 H322 H323 H327

H328

H325

FASTENERS NOT AFFECTEDHEAD ON THE VISIBLE SIDE

NOTE:

HEAD ON THE HIDDEN SIDE

N

F

LHRH

(110) 110

(111) 111

E

PROTECT THE CUTÜOUT AREA WITH MAT. No 04CMA2 AND MAT. No 04EAC2 02

02

CUTÜOUT

WET INSTALL THE FASTENERS WITH MAT. No 06AAA1 EXCEPT FOR HOLES H332 AND H333 01

PROTECT THE FASTENERS HEAD AND NUTS WITH MAT. No 06ABA1

DO SEALANT BEAD AROUND PARTS WITH MAT. No 06ABB1

APPLY MAT. No 06ABB1 BETWEEN PARTS

01

INBOARD

OUTBOARD

REWORK THE SURFACES WITH MAXIMUM OF THE 0.5 mm (0.020 in) 04

DURING THE INSTALLATION OF THE NEW FRAME FOOT

04

04

04

DD

D

D

MAX

5.552 mm

(0.218 in)

5.552 mm

(0.218 in)

5.552 mm

(0.218 in)

5.552 mm

(0.218 in)

5.552 mm

(0.218 in)

5.552 mm

(0.218 in)

5.552 mm

(0.218 in)

5.552 mm

(0.218 in)

HOLE

SYMBOL ITEM PART NUMBER DESCRIPTION HOLE DIAMETER MIN

5.512 mm

(0.217 in) (2) NUT ASNA2529Ü3

(1) SCREW EN6115V3A9 33

9

5.512 mm

(0.217 in) (2) NUT ASNA2529Ü3

(1) SCREW EN6115V3A10 43

9

5.512 mm

(0.217 in) (2) NUT ASNA2529Ü3

(1) SCREW EN6115V3A10 43

9

5.512 mm

(0.217 in) (2) NUT ASNA2529Ü3

(1) SCREW EN6115V3A11 44

9

5.512 mm

(0.217 in) (4) NUT ASNA2529Ü3

(3) SCREW EN6115V3A6 10

9

5.512 mm

(0.217 in) (4) NUT ASNA2529Ü3

(3) SCREW EN6115V3A7 8

9

5.512 mm

(0.217 in)

5.512 mm

(0.217 in)

(5)

(94)

NUT

SCREW

NUT

ASNA2529Ü3

EN6115V3A6

ASNA2529Ü3

(93) SCREW EN6115V3A6

10

9

10

9

OR

N

N

FN

F

N

N

D_SB_536177_5_KAAA_03_01

Figure A-FKAAA - Sheet 03

Replacement of the Frame foot FR46, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177REVISION No.: 00 - May 20/15 Page: 614

5

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

SERVICE BULLETIN

**CONF 003

C C

(80) (81)

FWD

9.886 mm

(0.389 in)

9.925 mm

NUT (0.391 in)

SCREW

ASNA2529Ü6

EN6114V6X17

HOLE

SYMBOL ITEM PART NUMBER DESCRIPTION

HOLE DIAMETER

MIN MAX

HEAD ON THE VISIBLE SIDE

NOTE:

12

52

N

8.692 mm

(0.342 in)

8.732 mm

NUT (0.344 in)

SCREW

NAS1726Ü5E

ASNA2001V5Ü12Y

14

50

8.692 mm

(0.342 in)

8.732 mm

NUT (0.344 in)

SCREW

ASNA2529Ü5

EN6114V5Y8

16

15

4.060 mm

(0.160 in)

4.170 mm

(0.164 in) (19) 19 ASNA2050DXJ4020 RIVET

E

03 USE EXISTING HOLES IN STRINGERS FOR THE INSTALLATION OF STIFFENERS

01 WET INSTALL THE FASTENERS WITH MAT. No 06AAA1 EXCEPT FOR HOLES H332 AND H333

PROTECT THE FASTENERS HEAD AND NUTS WITH MAT. No 06ABA1

DO SEALANT BEAD AROUND PARTS WITH MAT. No 06ABB1, APPLY MAT. No 06ABB1 BETWEEN PARTS

01

(4)

(3)

(4)

(3)

(4)

(3)

N

01

LH

RH

(110) 110

(111) 111

N

N

N

H337

H336

H334

H332 H333

H335

H339

H340

H338 H341

B B

(58)

(57)

LH

RH

FR46

03

01

STGR37

H315

H314

STGR37

(81)

(58)

(57)

LH

RH

(80)

05 05

FRAME FOOT

TYPICAL SECTION

D D

05 SPOTFACES TO BE REALIZED DURING INSTALLATION AFTER DRILLING OF PARTS TO DIAMETER

27 mm (1.063 in) FOR OLD FASTENERS DIAMETER 9.52 mm (0.375 in) AND TO DIAMETER 29 mm (1.142 in)

 FOR OLD FASTENERS DIAMETER 11.1 mm (0.437 in)

ELECTRICAL BONDING

D_SB_536177_5_KAAA_04_01

Figure A-FKAAA - Sheet 04

Replacement of the Frame foot FR46, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 615

5

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

SERVICE BULLETIN

**CONF 003

FASTENERS NOT AFFECTED

NOTE:

FR46

RH SYMMETRICAL

VIEW LOOKING AFT

LH SHOWN

5.512 mm

(0.217 in)

5.552 mm

NUT (0.218 in)

SCREW

ASNA2529Ü3

EN6115V3A7

HOLE

SYMBOL ITEM PART NUMBER DESCRIPTION

HOLE DIAMETER

MIN MAX

HEAD ON THE VISIBLE SIDE

9

8

N

5.512 mm

(0.217 in)

5.552 mm

NUT (0.218 in)

SCREW

ASNA2529Ü3

EN6115V3A6

9

10

5.512 mm

(0.217 in)

5.552 mm

NUT (0.218 in)

SCREW

ASNA2529Ü3

EN6115V3A5

9

17

5.512 mm

(0.217 in)

5.552 mm

(0.218 in)

01 WET INSTALL THE FASTENERS WITH MAT No 06AAA1 EXCEPT FOR HOLES H332 AND H333

PROTECT THE FASTENERS HEAD AND NUTS WITH MAT No 06ABA1

DO SEALANT BEAD AROUND PARTS WITH MAT No 06ABB1

APPLY MAT No 06ABB1 BETWEEN PARTS

(4)

(3)

(4)

(3)

(4)

(3)

F

NUT

SCREW

ASNA2529Ü3

EN6115V3A4

9

18

(4)

(3)

01

H350

STGR38

STGR39

H349

H348

H347

H346

H345

H344

H343

H342

G

N

N

N

N

FR46

FWD

(82)

(83)

H354

H353

H351

LH

RH

H352

G 01

INBOARD

OUTBOARD

D_SB_536177_5_KAAA_05_00

Figure A-FKAAA - Sheet 05

Replacement of the Frame foot FR46, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 616

5

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

SERVICE BULLETIN

**CONF 002

FR40

A

B

FR47

FR46

B

Z140

A

C

D

F

C

D

F

FR46

D_SB_536177_5_KAAB_01_00

Figure A-FKAAB - Sheet 01

Replacement of the Frame foot FR46, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 617

5

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

SERVICE BULLETIN

**CONF 002

RH SYMMETRICAL

VIEW LOOKING AFT

LH SHOWN

A A

F

W

D

C

(55)

01 WET INSTALL THE FASTENERS WITH MAT. No 06AAA1 EXCEPT FOR HOLES H332 AND H333

PROTECT THE FASTENERS HEAD AND NUTS WITH MAT. No 06ABA1

DO SEALANT BEAD AROUND PARTS WITH MAT. No 06ABB1

APPLY MAT. No 06ABB1 BETWEEN PARTS

01

NOTE:

A A

FR46

INBOARD

OUTBOARD

OR (76) 76

(56) 56

D_SB_536177_5_KAAB_02_01

Figure A-FKAAB - Sheet 02

Replacement of the Frame foot FR46, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 618

5

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

SERVICE BULLETIN

**CONF 002

B

B

STGR37

D

RH SYMMETRICAL

VIEW LOOKING AFT

LH SHOWN

FR46

C

C

(81)

H331

80

H321

H308 H307

H306

H320

H319

H304

H305

H318

H310

H309 H313

H317

H302

H303 H312

H311 H301

H300

H316 H324

H326 H329

H330 H322 H323 H327

H328

H325

FASTENERS NOT AFFECTEDHEAD ON THE VISIBLE SIDE

NOTE:

HEAD ON THE HIDDEN SIDE

N

F

LHRH

(110) 110

(111) 111

E

PROTECT THE CUTÜOUT AREA WITH MAT. No 04CMA2 AND MAT. No 04EAC2 02

02

CUTÜOUT

WET INSTALL THE FASTENERS WITH MAT. No 06AAA1 EXCEPT FOR HOLES H332 AND H333 01

PROTECT THE FASTENERS HEAD AND NUTS WITH MAT. No 06ABA1

DO SEALANT BEAD AROUND PARTS WITH MAT. No 06ABB1

APPLY MAT. No 06ABB1 BETWEEN PARTS

01

INBOARD

OUTBOARD

REWORK THE SURFACES WITH MAXIMUM OF THE 0.5 mm (0.020 in) 04

DURING THE INSTALLATION OF THE NEW FRAME FOOT

04

04

04

DD

D

D

MAX

5.552 mm

(0.218 in)

5.552 mm

(0.218 in)

5.552 mm

(0.218 in)

5.552 mm

(0.218 in)

5.552 mm

(0.218 in)

5.552 mm

(0.218 in)

HOLE

SYMBOL ITEM PART NUMBER DESCRIPTION HOLE DIAMETER MIN

5.512 mm

(0.217 in) (2) NUT ASNA2529Ü3

(1) SCREW EN6115V3A9 33

9

5.512 mm

(0.217 in) (2) NUT ASNA2529Ü3

(1) SCREW EN6115V3A10 43

9

5.512 mm

(0.217 in) (2) NUT ASNA2529Ü3

(1) SCREW EN6115V3A10 43

9

5.512 mm

(0.217 in) (2) NUT ASNA2529Ü3

(1) SCREW EN6115V3A11 44

9

5.512 mm

(0.217 in) (2) NUT ASNA2529Ü3

(1) SCREW EN6115V3A6 10

9

5.512 mm

(0.217 in) (2) NUT ASNA2529Ü3

(1) SCREW EN6115V3A7 8

9

N

N

FN

5.552 mm

(0.218 in)

5.512 mm

(0.217 in) (2) NUT ASNA2529Ü3

(1) SCREW EN6115V3A6

9

10

F

NN

D_SB_536177_5_KAAB_03_01

Figure A-FKAAB - Sheet 03

Replacement of the Frame foot FR46, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177REVISION No.: 00 - May 20/15 Page: 619

5

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

SERVICE BULLETIN

**CONF 002

10.282 mm

(0.405 in)

10.321 mm

NUT (0.406 in)

SCREW

ASNA2529Ü6

EN6114V6Y17

HOLE

SYMBOL ITEM PART NUMBER DESCRIPTION

HOLE DIAMETER

MIN MAX

HEAD ON THE VISIBLE SIDE

NOTE:

12

49

N

8.692 mm

(0.342 in)

8.732 mm

NUT (0.344 in)

SCREW

NAS1726Ü5E

ASNA2001V5Ü12Y

14

50

8.692 mm

(0.342 in)

8.692 mm

NUT (0.342 in)

SCREW

ASNA2529Ü5

EN6114V5Y8

16

15

4.060 mm

(0.160 in)

4.170 mm

(0.164 in) (19) 19 ASNA2050DXJ4020 RIVET

(2)

(1)

(2)

(1)

(2)

(1)

N

N

N

N

C C

(80) (81)

FWD

E 01 01

LH

RH

(110) 110

(111) 111

H337

H336

H334

H332 H333

H335

H339

H340

H338 H341

B B

(58)

(57)

LH

RH

FR46

03

01

STGR37

H315

H314

STGR37

(81)

(58)

(57)

LH

RH

(80)

05 05

FRAME FOOT

TYPICAL SECTION

D D

03 USE EXISTING HOLES IN STRINGERS FOR THE INSTALLATION OF STIFFENERS

01 WET INSTALL THE FASTENERS WITH MAT. No 06AAA1 EXCEPT FOR HOLES H332 AND H333

PROTECT THE FASTENERS HEAD AND NUTS WITH MAT. No 06ABA1

DO SEALANT BEAD AROUND PARTS WITH MAT. No 06ABB1, APPLY MAT. No 06ABB1 BETWEEN PARTS

05 SPOTFACES TO BE REALIZED DURING INSTALLATION AFTER DRILLING OF PARTS TO DIAMETER

27 mm (1.063 in) FOR OLD FASTENERS DIAMETER 9.52 mm (0.375 in) AND TO DIAMETER 29 mm (1.142 in)

 FOR OLD FASTENERS DIAMETER 11.1 mm (0.437 in)

ELECTRICAL BONDING

D_SB_536177_5_KAAB_04_01

Figure A-FKAAB - Sheet 04

Replacement of the Frame foot FR46, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 620

5

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

SERVICE BULLETIN

**CONF 002

FASTENERS NOT AFFECTED

NOTE:

FR46

RH SYMMETRICAL

VIEW LOOKING AFT

LH SHOWN

5.512 mm

(0.217 in)

5.552 mm

NUT (0.218 in)

SCREW

ASNA2529Ü3

EN6115V3A7

HOLE

SYMBOL ITEM PART NUMBER DESCRIPTION

HOLE DIAMETER

MIN MAX

HEAD ON THE VISIBLE SIDE

9

8

N

5.512 mm

(0.217 in)

5.552 mm

NUT (0.218 in)

SCREW

ASNA2529Ü3

EN6115V3A6

9

10

5.512 mm

(0.217 in)

5.552 mm

NUT (0.218 in)

SCREW

ASNA2529Ü3

EN6115V3A5

9

17

5.512 mm

(0.217 in)

5.552 mm

(0.218 in)

01 WET INSTALL THE FASTENERS WITH MAT No 06AAA1 EXCEPT FOR HOLES H332 AND H333

PROTECT THE FASTENERS HEAD AND NUTS WITH MAT No 06ABA1

DO SEALANT BEAD AROUND PARTS WITH MAT No 06ABB1

APPLY MAT No 06ABB1 BETWEEN PARTS

(4)

(3)

(4)

(3)

(4)

(3)

F

NUT

SCREW

ASNA2529Ü3

EN6115V3A4

9

18

(4)

(3)

01

H350

STGR38

STGR39

H349

H348

H347

H346

H345

H344

H343

H342

G

N

N

N

N

FR46

FWD

(82)

(83)

H354

H353

H351

LH

RH

H352

G 01

OUTBOARD

INBOARD

D_SB_536177_5_KAAB_05_00

Figure A-FKAAB - Sheet 05

Replacement of the Frame foot FR46, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 621

5

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

SERVICE BULLETIN

**CONF 001

FR40

A

B

FR47

FR46

B

Z140

A

C

D

F

C

D

F

FR46

D_SB_536177_5_KAAC_01_00

Figure A-FKAAC - Sheet 01

Replacement of the Frame foot FR46, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 622

5

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

SERVICE BULLETIN

**CONF 001

RH SYMMETRICAL

VIEW LOOKING AFT

LH SHOWN

A A

F

W

D

C

(55)

01 WET INSTALL THE FASTENERS WITH MAT. No 06AAA1 EXCEPT FOR HOLES H332 AND H333

PROTECT THE FASTENERS HEAD AND NUTS WITH MAT. No 06ABA1

DO SEALANT BEAD AROUND PARTS WITH MAT. No 06ABB1

APPLY MAT. No 06ABB1 BETWEEN PARTS

01

NOTE:

A A

FR46

INBOARD

OUTBOARD

OR (76) 76

(56) 56

D_SB_536177_5_KAAC_02_01

Figure A-FKAAC - Sheet 02

Replacement of the Frame foot FR46, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 623

5

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

SERVICE BULLETIN

**CONF 001

B

B

STGR37

D

RH SYMMETRICAL

VIEW LOOKING AFT

LH SHOWN

FR46

H331

H321

H308 H307

H306

H320

H319

H304

H305

H318

H310

H309 H313

H317

H302

H303 H312

H301 H311

H300

H316 H324

H326 H329

H330 H322 H323 H327

H328

H325

FASTENERS NOT AFFECTED

NOTE:

LH

RH

(110) 110

(111) 111

E

01 WET INSTALL THE FASTENERS WITH MAT. No 06AAA1 EXCEPT FOR HOLES H332 AND H333

PROTECT THE FASTENERS HEAD AND NUTS WITH MAT. No 06ABA1

DO SEALANT BEAD AROUND PARTS WITH MAT. No 06ABB1

APPLY MAT. No 06ABB1 BETWEEN PARTS

01

INBOARD

OUTBOARD

03 REWORK THE SURFACES WITH MAXIMUM OF THE 0.5 mm (0.020 in)

DURING THE INSTALLATION OF THE NEW FRAME FOOT

03

03

03

C

C

C

C

D_SB_536177_5_KAAC_03_01

Figure A-FKAAC - Sheet 03

Replacement of the Frame foot FR46, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 624

5

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

SERVICE BULLETIN

**CONF 001

5.113 mm

(0.201 in)

5.113 mm

(0.201 in)

5.152 mm

(0.203 in)

5.152 mm

(0.203 in) (5)

(94)

NUT

SCREW

NUT

ASNA2529Ü3

EN6115V3X6

ASNA2529Ü3

HOLE

SYMBOL ITEM PART NUMBER DESCRIPTION

HOLE DIAMETER

MIN MAX

(93) EN6115V3X6 SCREW

HEAD ON THE VISIBLE SIDE

NOTE:

9

25

9

25

5.113 mm

(0.201 in)

5.113 mm

(0.201 in)

5.152 mm

(0.203 in)

5.152 mm

(0.203 in) (5)

(94)

NUT

SCREW

NUT

ASNA2529Ü3

EN6115V3X5

ASNA2529Ü3

(93) EN6115V3X5 SCREW

9

23

9

23

5.113 mm

(0.201 in)

5.113 mm

(0.201 in)

5.152 mm

(0.203 in)

5.152 mm

(0.203 in) (5)

(94)

NUT

SCREW

NUT

ASNA2529Ü3

EN6115V3X7

ASNA2529Ü3

(93) EN6115V3X7 SCREW

9

24

9

24

5.113 mm

(0.201 in)

5.152 mm

(4) ASNA2529Ü3 NUT (0.203 in)

(3) EN6115V3X6 SCREW

9

25

5.113 mm

(0.201 in)

5.152 mm

(4) ASNA2529Ü3 NUT (0.203 in)

(3) EN6115V3X7 SCREW

9

24

5.113 mm

(0.201 in)

5.152 mm

(4) ASNA2529Ü3 NUT (0.203 in)

(3) EN6115V3X6 SCREW

9

25

OR

OR

OR

HEAD ON THE HIDDEN SIDE F

N

F

N

N

N

N

N

D_SB_536177_5_KAAC_04_00

Figure A-FKAAC - Sheet 04

Replacement of the Frame foot FR46, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 625

5

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

SERVICE BULLETIN

**CONF 001

9.886 mm

(0.389 in)

9.925 mm

NUT (0.391 in)

SCREW

ASNA2529Ü6

EN6114V6X17

HOLE

SYMBOL ITEM PART NUMBER DESCRIPTION

HOLE DIAMETER

MIN MAX

12

52

8.296 mm

(0.327 in)

8.335 mm

NUT (0.328 in)

SCREW

NAS1726Ü5E

ASNA2001V5Ü12X

14

53

8.296 mm

(0.327 in)

8.335 mm

NUT (0.328 in)

SCREW

ASNA2529Ü5

EN6114V5X8

16

28

4.060 mm

(0.160 in)

4.170 mm

(0.164 in) (19) 19 ASNA2050DXJ4020 RIVET

(4)

(3)

(4)

(3)

(4)

(3)

N

N

N

FWD

E 01

LH

RH

(110) 110

(111) 111

H337

H336

H334

H332 H333

H335

H339

H340

H338 H341

B B

(58)

(57)

LH

RH

01

N

FR46

STGR37

02

H315

H314

04 04

FRAME FOOT

TYPICAL SECTION

C C

HEAD ON THE VISIBLE SIDE

NOTE:

N

02 USE EXISTING HOLES IN STRINGERS FOR THE INSTALLATION OF STIFFENERS

01 WET INSTALL THE FASTENERS WITH MAT. No 06AAA1 EXCEPT FOR HOLES H332 AND H333

PROTECT THE FASTENERS HEAD AND NUTS WITH MAT. No 06ABA1

DO SEALANT BEAD AROUND PARTS WITH MAT. No 06ABB1, APPLY MAT. No 06ABB1 BETWEEN PARTS

04 SPOTFACES TO BE REALIZED DURING INSTALLATION AFTER DRILLING OF PARTS TO DIAMETER

27 mm (1.063 in) FOR OLD FASTENERS DIAMETER 9.52 mm (0.375 in) AND TO DIAMETER 29 mm (1.142 in)

 FOR OLD FASTENERS DIAMETER 11.1 mm (0.437 in)

ELECTRICAL BONDING

D_SB_536177_5_KAAC_05_01

Figure A-FKAAC - Sheet 05

Replacement of the Frame foot FR46, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 626

5

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

SERVICE BULLETIN

**CONF 001

FASTENERS NOT AFFECTED

NOTE:

FR46

RH SYMMETRICAL

VIEW LOOKING AFT

LH SHOWN

5.113 mm

(0.201 in)

5.152 mm

NUT (0.203 in)

SCREW

ASNA2529Ü3

EN6115V3X7

HOLE

SYMBOL ITEM PART NUMBER DESCRIPTION

HOLE DIAMETER

MIN MAX

HEAD ON THE VISIBLE SIDE

9

24

N

5.113 mm

(0.201 in)

5.152 mm

NUT (0.203 in)

SCREW

ASNA2529Ü3

EN6115V3X6

9

25

5.113 mm

(0.201 in)

5.152 mm

NUT (0.203 in)

SCREW

ASNA2529Ü3

EN6115V3X5

9

23

5.113 mm

(0.201 in)

5.152 mm

(0.203 in)

01 WET INSTALL THE FASTENERS WITH MAT No 06AAA1 EXCEPT FOR HOLES H332 AND H333

PROTECT THE FASTENERS HEAD AND NUTS WITH MAT No 06ABA1

DO SEALANT BEAD AROUND PARTS WITH MAT No 06ABB1

APPLY MAT No 06ABB1 BETWEEN PARTS

(4)

(3)

(4)

(3)

(4)

(3)

F

NUT

SCREW

ASNA2529Ü3

EN6115V3X4

9

29

(4)

(3)

01

H350

STGR38

STGR39

H349

H348

H347

H346

H345

H344

H343

H342

G

N

N

N

N

FR46

FWD

(82)

(83)

H354

H353

H351

LH

RH

H352

G 01

OUTBOARD

INBOARD

D_SB_536177_5_KAAC_06_00

Figure A-FKAAC - Sheet 06

Replacement of the Frame foot FR46, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 627

5

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

SERVICE BULLETIN

**CONF 001, 003

FR40

A

B

FR41

FR47

FR41

B

Z140

A

C

C

D_SB_536177_5_LAAA_01_00

Figure A-FLAAA - Sheet 01

Removal/Installation of the Gussets at FR41, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 628

5

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

SERVICE BULLETIN

**CONF 001, 003

FR41

(122)

(123)

LH

RH

B B

FWD

C

FR41

LH SHOWN 

RH SYMMETRICAL

A A

A

A

VIEW LOOKING DOWN

FRAME FOOT

(120)

(121)

LH

RH

D_SB_536177_5_LAAA_02_01

Figure A-FLAAA - Sheet 02

Removal/Installation of the Gussets at FR41, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 629

5

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

SERVICE BULLETIN

**CONF 001, 003

21

30

NUT

SCREW

ASNA2529Ü4

HOLE

SYMBOL ITEM PART NUMBER DESCRIPTION

HOLE DIAMETER

MIN MAX

EN6114V4X8 6.706 mm

(0.264 in)

6.747 mm

(0.266 in)

(3)

(4)

12

26

NUT

SCREW

ASNA2529Ü6

EN6114V6X14 9.886 mm

(0.389 in)

9.925 mm

(0.391 in)

(3)

F (4)

F

21

31

NUT

SCREW

ASNA2529Ü4

EN6114V4X10 6.706 mm

(0.264 in)

6.747 mm

(0.266 in)

(3)

F (4)

01 FOR THE POSITIONING OF THE GUSSET, RESPECT THE THEORICAL

DISTANCE OF 2 mm (0.079 in) BETWEEN THE GUSSET AND THE FRAME FOOT

02 FOR THE POSITIONING OF THE GUSSET, RESPECT THE THEORICAL

DISTANCE OF 1.3 mm (0.051 in) BETWEEN THE GUSSET AND THE FRAME FOOT

NOTE:

HEAD ON THE HIDDEN SIDE F

B B

FWD

FR41

H47

H25 H24

H48

01 02

D_SB_536177_5_LAAA_03_01

Figure A-FLAAA - Sheet 03

Removal/Installation of the Gussets at FR41, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 630

5

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

SERVICE BULLETIN

**CONF 002

FR40

A

B

FR41

FR47

FR41

B

Z140

A

C

C

D_SB_536177_5_LAAB_01_00

Figure A-FLAAB - Sheet 01

Removal/Installation of the Gussets at FR41, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 631

5

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

SERVICE BULLETIN

**CONF 002

FR41

(122)

(123)

LH

RH

B B

FWD

C

FR41

LH SHOWN 

RH SYMMETRICAL

A A

A

A

VIEW LOOKING DOWN

FRAME FOOT

(120)

(121)

LH

RH

D_SB_536177_5_LAAB_02_01

Figure A-FLAAB - Sheet 02

Removal/Installation of the Gussets at FR41, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 632

5

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

SERVICE BULLETIN

**CONF 002

21

20

NUT

SCREW

ASNA2529Ü4

HOLE

SYMBOL ITEM PART NUMBER DESCRIPTION

HOLE DIAMETER

MIN MAX

EN6114V4Y9 7.102 mm

(0.280 in)

7.141 mm

(0.281 in)

(3)

(4)

21

22

NUT

SCREW

ASNA2529Ü4

EN6114V4Y10 7.102 mm

(0.280 in)

7.141 mm

(0.281 in)

(3)

(4)

12

11

NUT

SCREW

ASNA2529Ü6

EN6114V6Y14 10.282 mm

(0.405 in)

10.321 mm

(0.406 in)

(1)

F (2)

F

F

NOTE:

HEAD ON THE HIDDEN SIDE F

H25 H24

FWD B B

FR41

02

01

01 FOR THE POSITIONING OF THE GUSSET RESPECT THE THEORICAL DISTANCE OF 2 mm (0.079 in)

BETWEEN THE GUSSET AND THE FRAME FOOT

02 FOR THE POSITIONING OF THE GUSSET RESPECT THE THEORICAL DISTANCE OF 1.3 mm (0.051 in)

BETWEEN THE GUSSET AND THE FRAME FOOT

H47 H48

D_SB_536177_5_LAAB_03_01

Figure A-FLAAB - Sheet 03

Removal/Installation of the Gussets at FR41, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 633

5

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

SERVICE BULLETIN

**CONF 001, 003

FR40

A

B

FR42

FR47

FR42

B

Z140

A

C

C

D_SB_536177_5_NAAA_01_00

Figure A-FNAAA - Sheet 01

Removal/Installation of the Gussets at FR42, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 634

5

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

SERVICE BULLETIN

**CONF 001, 003

FR42

(124)

(125)

LH

RH

(126)

(127)

LH

RH

B B

FWD A A

VIEW LOOKING DOWN

C

FR42

LH SHOWN 

RH SYMMETRICAL

A

A

FRAME FOOT

D_SB_536177_5_NAAA_02_01

Figure A-FNAAA - Sheet 02

Removal/Installation of the Gussets at FR42, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 635

5

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

SERVICE BULLETIN

**CONF 001, 003

NOTE:

21

30

NUT

SCREW

ASNA2529Ü4

HOLE

SYMBOL ITEM PART NUMBER DESCRIPTION

HOLE DIAMETER

MIN MAX

EN6114V4X8 6.706 mm

(0.264 in)

6.747 mm

(0.265 in)

(3)

(4)

21

31

NUT

SCREW

ASNA2529Ü4

EN6114V4X10 6.706 mm

(0.264 in)

6.747 mm

(0.265 in)

(3)

(4)

HEAD ON THE HIDDEN SIDE F

12

35

NUT

SCREW

ASNA2529Ü6

EN6114V6X13 9.886 mm

(0.389 in)

9.925 mm

(0.391 in)

(3)

(4)

F

F

F

B B

FR42

02

01

H118

H92 H91

H119

FWD

01 FOR THE POSITIONING OF THE GUSSET RESPECT THE THEORICAL DISTANCE OF 2 mm (0.079 in)

BETWEEN THE GUSSET AND THE FRAME FOOT

02 FOR THE POSITIONING OF THE GUSSET RESPECT THE THEORICAL DISTANCE OF 1.3 mm (0.051 in)

BETWEEN THE GUSSET AND THE FRAME FOOT D_SB_536177_5_NAAA_03_01

Figure A-FNAAA - Sheet 03

Removal/Installation of the Gussets at FR42, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 636

5

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

SERVICE BULLETIN

**CONF 002

FR40

A

B

FR42

FR47

FR42

B

Z140

A

C

C

D_SB_536177_5_NAAB_01_00

Figure A-FNAAB - Sheet 01

Removal/Installation of the Gussets at FR42, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 637

5

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

SERVICE BULLETIN

**CONF 002

FR42

(126)

(127)

LH

RH

B B

FWD

C

FR42

LH SHOWN 

RH SYMMETRICAL

A A

A

A

VIEW LOOKING DOWN

FRAME FOOT

(124)

(125)

LH

RH

D_SB_536177_5_NAAB_02_01

Figure A-FNAAB - Sheet 02

Removal/Installation of the Gussets at FR42, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 638

5

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

SERVICE BULLETIN

**CONF 002

NOTE:

21

20

NUT

SCREW

ASNA2529Ü4

HOLE

SYMBOL ITEM PART NUMBER DESCRIPTION

HOLE DIAMETER

MIN MAX

EN6114V4Y9 7.141 mm

(0.281 in)

7.102 mm

(0.279 in)

(3)

(4)

21

22

NUT

SCREW

ASNA2529Ü4

EN6114V4Y10 7.141 mm

(0.281 in)

7.102 mm

(0.279 in)

(3)

(4)

HEAD ON THE HIDDEN SIDE

12

34

NUT

SCREW

ASNA2529Ü6

EN6114V6Y13 10.282 mm

(0.405 in)

10.321 mm

(0.406 in)

(1)

(2)

F

F

H118

H92 H91

H119

FWD B B

FR42

02

01

01 FOR THE POSITIONING OF THE GUSSET RESPECT THE THEORICAL DISTANCE OF 2 mm (0.079 in)

BETWEEN THE GUSSET AND THE FRAME FOOT

02 FOR THE POSITIONING OF THE GUSSET RESPECT THE THEORICAL DISTANCE OF 1.3 mm (0.051 in)

BETWEEN THE GUSSET AND THE FRAME FOOT

F

F

D_SB_536177_5_NAAB_03_01

Figure A-FNAAB - Sheet 03

Removal/Installation of the Gussets at FR42, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 639

5

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

SERVICE BULLETIN

**CONF 001, 003

FR40

A

B

FR47

FR43

B

Z140

A

C

C

FR43

D_SB_536177_5_PAAA_01_00

Figure A-FPAAA - Sheet 01

Removal/Installation of the Gussets at FR43, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 640

5

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

SERVICE BULLETIN

**CONF 001, 003

FR43

(128)

(129)

LH

RH

(130)

(131)

LH

RH

B B

FWD

C

FR43

LH SHOWN 

RH SYMMETRICAL

A A

A

A

FRAME FOOT

D_SB_536177_5_PAAA_02_01

Figure A-FPAAA - Sheet 02

Removal/Installation of the Gussets at FR43, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 641

5

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

SERVICE BULLETIN

**CONF 001, 003

21

30

NUT

SCREW

ASNA2529Ü4

HOLE

SYMBOL ITEM PART NUMBER DESCRIPTION

HOLE DIAMETER

MIN MAX

EN6114V4X8 6.706 mm

(0.264 in)

6.747 mm

(0.265 in)

(3)

(4)

NOTE:

16

41

NUT

SCREW

ASNA2529Ü5

EN6114V5X10 8.296 mm

(0.326 in)

8.335 mm

(0.328 in)

(3)

(4)

B B

FWD

12

26

NUT

SCREW

ASNA2529Ü6

EN6114V6X14 9.886 mm

(0.389 in)

9.925 mm

(0.391 in)

(3)

F (4)

HEAD ON THE HIDDEN SIDE F

H170

H151 H150

H171

FR43

02

01

F

01 FOR THE POSITIONING OF THE GUSSET RESPECT THE THEORICAL DISTANCE OF 2 mm (0.079 in)

BETWEEN THE GUSSET AND THE FRAME FOOT

02 FOR THE POSITIONING OF THE GUSSET RESPECT THE THEORICAL DISTANCE OF 1.3 mm (0.051 in)

BETWEEN THE GUSSET AND THE FRAME FOOT

F

D_SB_536177_5_PAAA_03_01

Figure A-FPAAA - Sheet 03

Removal/Installation of the Gussets at FR43, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 642

5

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

SERVICE BULLETIN

**CONF 002

FR40

A

B

FR47

FR43

B

Z140

A

C

C

FR43

D_SB_536177_5_PAAB_01_00

Figure A-FPAAB - Sheet 01

Removal/Installation of the Gussets at FR43, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 643

5

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

SERVICE BULLETIN

**CONF 002

FR43

(130)

(131)

LH

RH

B B

FWD

C

FR43

LH SHOWN 

RH SYMMETRICAL

A A

A

A

VIEW LOOKING DOWN

FRAME FOOT

(128)

(129)

LH

RH

D_SB_536177_5_PAAB_02_01

Figure A-FPAAB - Sheet 02

Removal/Installation of the Gussets at FR43, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 644

5

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

SERVICE BULLETIN

**CONF 002

16

37

NUT

SCREW

ASNA2529Ü5

HOLE

SYMBOL ITEM PART NUMBER DESCRIPTION

HOLE DIAMETER

MIN MAX

EN6114V5Y10 8.732 mm

(0.344 in)

8.692 mm

(0.342 in)

(3)

(4)

NOTE:

21

20

NUT

SCREW

ASNA2529Ü4

EN6114V4Y9 7.141 mm

(0.281 in)

7.102 mm

(0.279 in)

(3)

(4)

12

11

NUT

SCREW

ASNA2529Ü6

EN6114V6Y14 10.282 mm

(0.405 in)

10.321 mm

(0.406 in)

(1)

(2)

HEAD ON THE HIDDEN SIDE F

F

H170 H171

FWD B B

FR43

02

01

01 FOR THE POSITIONING OF THE GUSSET RESPECT THE THEORICAL DISTANCE OF 2 mm (0.079 in)

BETWEEN THE GUSSET AND THE FRAME FOOT

02 FOR THE POSITIONING OF THE GUSSET RESPECT THE THEORICAL DISTANCE OF 1.3 mm (0.051 in)

BETWEEN THE GUSSET AND THE FRAME FOOT

H151 H150

F

F

D_SB_536177_5_PAAB_03_01

Figure A-FPAAB - Sheet 03

Removal/Installation of the Gussets at FR43, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 645

5

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

SERVICE BULLETIN

**CONF 001, 003

Z140

A

C

C

FR44

B

FR44

A

B

FR40

FR47

D_SB_536177_5_QAAA_01_00

Figure A-FQAAA - Sheet 01

Removal/Installation of the Gussets at FR44, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 646

5

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

SERVICE BULLETIN

**CONF 001, 003

FR44

(132)

(133)

LH

RH

(134)

(135)

LH

RH

B B

FWD

C

FR44

LH SHOWN 

RH SYMMETRICAL

A A

VIEW LOOKING DOWN

A

A

FRAME FOOT

D_SB_536177_5_QAAA_02_01

Figure A-FQAAA - Sheet 02

Removal/Installation of the Gussets at FR44, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 647

5

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

SERVICE BULLETIN

**CONF 001, 003

NOTE:

HEAD ON THE HIDDEN SIDE F

HOLE

SYMBOL ITEM PN DESCRIPTION

HOLE DIAMETER

MIN MAX

(3)

(4) ASNA2529Ü5

 EN6114V5X10

NUT

41 SCREW

16

8.335 mm

(0.328 in)

8.296 mm

(0.326 in)

(3)

(4) ASNA2529Ü6

EN6114V6X14

NUT

26 SCREW

12

(3)

(4) ASNA2529Ü5

 EN6114V5X8

NUT

28 SCREW

16

9.925 mm

(0.391 in)

9.886 mm

(0.389 in)

F

F

F

8.335 mm

(0.328 in)

8.296 mm

(0.326 in)

B B

FWD

02

01

FR44

H223 H224

H204 H203

01 FOR THE POSITIONING OF THE GUSSET RESPECT THE THEORICAL DISTANCE OF 2 mm (0.079 in)

BETWEEN THE GUSSET AND THE FRAME FOOT

02 FOR THE POSITIONING OF THE GUSSET RESPECT THE THEORICAL DISTANCE OF 1.3 mm (0.051 in)

BETWEEN THE GUSSET AND THE FRAME FOOT D_SB_536177_5_QAAA_03_01

Figure A-FQAAA - Sheet 03

Removal/Installation of the Gussets at FR44, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 648

5

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

SERVICE BULLETIN

**CONF 002

Z140

A

C

C

FR44

B

FR44

A

B

FR40

FR47

D_SB_536177_5_QAAB_01_00

Figure A-FQAAB - Sheet 01

Removal/Installation of the Gussets at FR44, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 649

5

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

SERVICE BULLETIN

**CONF 002

FR44

(134)

(135)

LH

RH

B B

FWD

C

FR44

LH SHOWN 

RH SYMMETRICAL

A A

A

A

VIEW LOOKING DOWN

FRAME FOOT

(132)

(133)

LH

RH

D_SB_536177_5_QAAB_02_01

Figure A-FQAAB - Sheet 02

Removal/Installation of the Gussets at FR44, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 650

5

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

SERVICE BULLETIN

**CONF 002

HOLE

SYMBOL ITEM PN DESCRIPTION

HOLE DIAMETER

MIN MAX

(3)

(4) ASNA2529Ü5

 EN6114V5Y10

NUT

37 SCREW

16

8.692 mm

(0.342 in)

8.732 mm

(0.344 in)

(1)

(2) ASNA2529Ü6

EN6114V6Y14

NUT

11 SCREW

12

10.321 mm

(0.406 in)

10.282 mm

(0.405 in)

NOTE:

HEAD ON THE HIDDEN SIDE F

H223

H204 H203

H224

FWD B B

FR44

02

01

01 FOR THE POSITIONING OF THE GUSSET RESPECT THE THEORICAL DISTANCE OF 2 mm (0.079 in)

BETWEEN THE GUSSET AND THE FRAME FOOT

02 FOR THE POSITIONING OF THE GUSSET RESPECT THE THEORICAL DISTANCE OF 1.3 mm (0.051 in)

BETWEEN THE GUSSET AND THE FRAME FOOT

F

F

D_SB_536177_5_QAAB_03_01

Figure A-FQAAB - Sheet 03

Removal/Installation of the Gussets at FR44, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 651

5

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

SERVICE BULLETIN

**CONF 001, 003

A

Z140

A

FR45

B

C

C

FR40

B

FR47

FR45

D_SB_536177_5_TAAA_01_00

Figure A-FTAAA - Sheet 01

Removal/Installation of the Gussets at FR45, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 652

5

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

SERVICE BULLETIN

**CONF 001, 003

C

FR45

LH SHOWN 

RH SYMMETRICAL

A

A

FRAME FOOT

B B

FWD

A A

FR45

(136)

(137)

LH

RH

(138)

(139)

LH

RH

D_SB_536177_5_TAAA_02_01

Figure A-FTAAA - Sheet 02

Removal/Installation of the Gussets at FR45, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 653

5

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

SERVICE BULLETIN

**CONF 001, 003

NOTE:

HEAD ON THE HIDDEN SIDE

F

F

8.296 mm

(0.326 in)

8.335 mm

NUT (0.328 in)

SCREW

ASNA2529Ü5

EN6114V5X10

HOLE

SYMBOL ITEM PART NUMBER DESCRIPTION

HOLE DIAMETER

MIN MAX

16

41

9.886 mm

(0.389 in)

9.925 mm

NUT (0.391 in)

SCREW

ASNA2529Ü6

EN6114V6X14

12

26

8.296 mm

(0.326 in)

8.335 mm

NUT (0.328 in)

SCREW

ASNA2529Ü5

EN6114V5X8

16

28

(4)

(3)

(4)

(3)

(4)

(3)

F

F

B B

FWD

02

01

FR45

H270 H269

H286 H287

01 FOR THE POSITIONING OF THE GUSSET RESPECT THE THEORICAL DISTANCE OF 2 mm (0.079 in)

BETWEEN THE GUSSET AND THE FRAME FOOT

02 FOR THE POSITIONING OF THE GUSSET RESPECT THE THEORICAL DISTANCE OF 1.3 mm (0.051 in)

BETWEEN THE GUSSET AND THE FRAME FOOT

D_SB_536177_5_TAAA_03_01

Figure A-FTAAA - Sheet 03

Removal/Installation of the Gussets at FR45, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 654

5

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

SERVICE BULLETIN

**CONF 002

A

Z140

A

FR45

B

C

C

FR40

B

FR47

FR45

D_SB_536177_5_TAAB_01_00

Figure A-FTAAB - Sheet 01

Removal/Installation of the Gussets at FR45, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 655

5

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

SERVICE BULLETIN

**CONF 002

FR45

(138)

(139)

LH

RH

B B

FWD

C

FR45

LH SHOWN 

RH SYMMETRICAL

A A

A

A

VIEW LOOKING DOWN

FRAME FOOT

(136)

(137)

LH

RH

D_SB_536177_5_TAAB_02_01

Figure A-FTAAB - Sheet 02

Removal/Installation of the Gussets at FR45, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 656

5

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

SERVICE BULLETIN

**CONF 002

NOTE:

HEAD ON THE HIDDEN SIDE F

NUT

SCREW

ASNA2529Ü5

EN6114V5Y10

HOLE

SYMBOL ITEM PART NUMBER DESCRIPTION

HOLE DIAMETER

MIN MAX

16

37

NUT

SCREW

ASNA2529Ü6

EN6114V6Y14

12

11

(4)

(3)

(2)

(1)

F

F

8.732 mm

(0.344 in)

8.692 mm

(0.342 in)

9.886 mm

(0.389 in)

9.925 mm

(0.391 in)

H286

H270 H269

H287

FWD B B

FR45

02

01

01 FOR THE POSITIONING OF THE GUSSET RESPECT THE THEORICAL DISTANCE OF 2 mm (0.079 in)

BETWEEN THE GUSSET AND THE FRAME FOOT

02 FOR THE POSITIONING OF THE GUSSET RESPECT THE THEORICAL DISTANCE OF 1.3 mm (0.051 in)

BETWEEN THE GUSSET AND THE FRAME FOOT

D_SB_536177_5_TAAB_03_01

Figure A-FTAAB - Sheet 03

Removal/Installation of the Gussets at FR45, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 657

5

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

SERVICE BULLETIN

**CONF 001, 003

C

FR40

A

B

FR47

FR46

Z140

A

FR46

B

C

D_SB_536177_5_UAAA_01_00

Figure A-FUAAA - Sheet 01

Removal/Installation of the Gussets at FR46, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 658

5

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

SERVICE BULLETIN

**CONF 001, 003

C

FR46

LH SHOWN 

RH SYMMETRICAL

A

A

FRAME FOOT

B B

FR46

(140)

(141)

LH

RH

(142)

(143)

LH

RH

FWD A A

VIEW LOOKING DOWN

D_SB_536177_5_UAAA_02_01

Figure A-FUAAA - Sheet 02

Removal/Installation of the Gussets at FR46, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 659

5

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

SERVICE BULLETIN

**CONF 001, 003

HOLE

SYMBOL ITEM PART NUMBER DESCRIPTION

HOLE DIAMETER

MIN MAX

NOTE:

HEAD ON THE HIDDEN SIDE

16

54

NUT

SCREW

ASNA2529Ü5

EN6114V5X12 8.296 mm

(0.326 in)

8.335 mm

(0.328 in)

NUT

SCREW

ASNA2529Ü6

EN6114V6X14 9.886 mm

(0.382 in)

9.925 mm

(0.391 in)

(3)

(4)

26

12

(3)

(4)

NUT

SCREW

ASNA2529Ü6

EN6114V6X17 9.886 mm

(0.389 in)

9.925 mm

(0.391 in)

(3)

(4)

52

12

F

F

F

F

B B

FWD

02

01

FR46

H355

H333 H332

H356

01 FOR THE POSITIONING OF THE GUSSET RESPECT THE THEORICAL DISTANCE OF 2 mm (0.079 in)

BETWEEN THE GUSSET AND THE FRAME FOOT

02 FOR THE POSITIONING OF THE GUSSET RESPECT THE THEORICAL DISTANCE OF 1.3 mm (0.051 in)

BETWEEN THE GUSSET AND THE FRAME FOOT D_SB_536177_5_UAAA_03_01

Figure A-FUAAA - Sheet 03

Removal/Installation of the Gussets at FR46, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 660

5

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

SERVICE BULLETIN

**CONF 002

C

FR40

A

B

FR47

FR46

Z140

A

FR46

B

C

D_SB_536177_5_UAAB_01_00

Figure A-FUAAB - Sheet 01

Removal/Installation of the Gussets at FR46, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 661

5

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

SERVICE BULLETIN

**CONF 002

FR46

(142)

(143)

LH

RH

B B

FWD

C

FR46

LH SHOWN 

RH SYMMETRICAL

A A

A

A

VIEW LOOKING DOWN

FRAME FOOT

(140)

(141)

LH

RH

D_SB_536177_5_UAAB_02_01

Figure A-FUAAB - Sheet 02

Removal/Installation of the Gussets at FR46, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 662

5

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

SERVICE BULLETIN

**CONF 002

HOLE

SYMBOL ITEM PART NUMBER DESCRIPTION

HOLE DIAMETER

MIN MAX

NOTE:

HEAD ON THE HIDDEN SIDE

16

51

NUT

SCREW

ASNA2529Ü5

EN6114V5Y12 8.732 mm

(0.344 in)

8.692 mm

(0.342 in)

12

11

NUT

SCREW

ASNA2529Ü6

EN6114V6Y14 10.282 mm

(0.405 in)

10.321 mm

(0.406 in)

(3)

(3)

(4)

(4)

NUT

SCREW

ASNA2529Ü6

EN6114V6Y17 10.282 mm

(0.405 in)

10.321 mm

(0.406 in)

(1)

(2)

49

12

F

H335

H333 H332

H356

FWD B B

FR46

02

01

01 FOR THE POSITIONING OF THE GUSSET RESPECT THE THEORICAL DISTANCE OF 2 mm (0.079 in)

BETWEEN THE GUSSET AND THE FRAME FOOT

02 FOR THE POSITIONING OF THE GUSSET RESPECT THE THEORICAL DISTANCE OF 1.3 mm (0.051 in)

BETWEEN THE GUSSET AND THE FRAME FOOT

F

F

F

D_SB_536177_5_UAAB_03_01

Figure A-FUAAB - Sheet 03

Removal/Installation of the Gussets at FR46, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 663

5

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

SERVICE BULLETIN

**CONF 001 thru 003

FR41

FR42

FR43

FR44

FR45

FR46

FR47

FR40

A

Z140

A

RH SHOWN

LH SYMMETRICAL

FWD

STGR35

STGR39

STGR40

C D E F G H

FR41 FR42 FR43 FR44 FR45 FR46

B

B

B

D_SB_536177_5_VAAA_01_01

Figure A-FVAAA - Sheet 01

Removal/Installation of the Fasteners from FR41 to FR46, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 664

5

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

SERVICE BULLETIN

**CONF 001 thru 003

A

A

RH SHOWN

LH SYMMETRICAL

STRINGER DATUM

HOLE

SYMBOL ITEM PART NUMBER DESCRIPTION

HOLE DIAMETER

MIN MAX

RIVET

ASNA2529Ü3

 EN6114V3X5

NUT

SCREW

EN6080D6XÜ32 RIVET

5.630 mm

(0.221 in)

5.530 mm

(0.218 in)

5.152 mm

(0.203 in)

5.113 mm

(0.201 in)

5.190 mm

(0.204 in)

5.130 mm

(0.202 in)

NOTE:

HEAD ON THE HIDDEN SIDE F

01 PROTECT THE FASTENERS WITH MATERIAL No 06ABA1

F

OR

(5) ASNA2019Ü56Ü25

(3)

(4)

(19)

90

91

9

92

01

FR41

TYPICAL SECTION

STGR35

STGR36

STGR37

STGR38

STGR39

A A

FR41 A

A

A

A

A

A

A

C A

F

D_SB_536177_5_VAAA_02_00

Figure A-FVAAA - Sheet 02

Removal/Installation of the Fasteners from FR41 to FR46, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 665

5

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

SERVICE BULLETIN

**CONF 001 thru 003

A

A

RH SHOWN

LH SYMMETRICAL

STRINGER DATUM

HOLE

SYMBOL ITEM PART NUMBER DESCRIPTION

HOLE DIAMETER

MIN MAX

RIVET

ASNA2529Ü3

 EN6114V3X5

NUT

SCREW

EN6080D6XÜ32 RIVET

5.630 mm

(0.221 in)

5.530 mm

(0.218 in)

5.152 mm

(0.203 in)

5.113 mm

(0.201 in)

5.190 mm

(0.204 in)

5.130 mm

(0.202 in)

NOTE:

HEAD ON THE HIDDEN SIDE F

01 PROTECT THE FASTENERS WITH MATERIAL No 06ABA1

OR

ASNA2019Ü56Ü25

01

FR42

TYPICAL SECTION

STGR36

STGR37

STGR38

STGR39

A A

A

A

A

A

A

A

FR42

D

(5)

(3)

(4)

(19)

90

91

9

92

F

F

D_SB_536177_5_VAAA_03_00

Figure A-FVAAA - Sheet 03

Removal/Installation of the Fasteners from FR41 to FR46, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 666

5

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

SERVICE BULLETIN

**CONF 001 thru 003

A

A

RH SHOWN

LH SYMMETRICAL

STRINGER DATUM

HOLE

SYMBOL ITEM PART NUMBER DESCRIPTION

HOLE DIAMETER

MIN MAX

RIVET

ASNA2529Ü3

 EN6114V3X6

NUT

SCREW

EN6080D6XÜ32 RIVET

5.630 mm

(0.221 in)

5.530 mm

(0.218 in)

5.152 mm

(0.203 in)

5.113 mm

(0.201 in)

5.190 mm

(0.204 in)

5.130 mm

(0.202 in)

NOTE:

HEAD ON THE HIDDEN SIDE F

01 PROTECT THE FASTENERS WITH MATERIAL No 06ABA1

OR

ASNA2019Ü56Ü25

01

FR43

STGR36

STGR37

STGR38

STGR39

A A

A

A

A

A

A

A

FR43

E

(5)

(3)

(4)

(19)

90

47

9

92

TYPICAL SECTION

F

F

D_SB_536177_5_VAAA_04_00

Figure A-FVAAA - Sheet 04

Removal/Installation of the Fasteners from FR41 to FR46, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 667

5

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

SERVICE BULLETIN

**CONF 001 thru 003

A

A

RH SHOWN

LH SYMMETRICAL

STRINGER DATUM

HOLE

SYMBOL ITEM PART NUMBER DESCRIPTION

HOLE DIAMETER

MIN MAX

RIVET

ASNA2529Ü3

 EN6114V3X5

NUT

SCREW

EN6080D6XÜ32 RIVET

5.630 mm

(0.221 in)

5.530 mm

(0.218 in)

5.152 mm

(0.203 in)

5.113 mm

(0.201 in)

5.190 mm

(0.204 in)

5.130 mm

(0.202 in)

NOTE:

HEAD ON THE HIDDEN SIDE F

01 PROTECT THE FASTENERS WITH MATERIAL No 06ABA1

OR

ASNA2019Ü56Ü25

01

FR44

TYPICAL SECTION

STGR36

STGR37

STGR38

STGR39

A A

A

A

A

A

A

A

FR44

(5)

(3)

(4)

(19)

90

91

9

92

F

F

F

D_SB_536177_5_VAAA_05_00

Figure A-FVAAA - Sheet 05

Removal/Installation of the Fasteners from FR41 to FR46, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 668

5

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

SERVICE BULLETIN

**CONF 001 thru 003

A

A

RH SHOWN

LH SYMMETRICAL

STRINGER DATUM

HOLE

SYMBOL ITEM PART NUMBER DESCRIPTION

HOLE DIAMETER

MIN MAX

RIVET

ASNA2529Ü3

 EN6114V3X6

NUT

SCREW

EN6080D6XÜ32 RIVET

5.630 mm

(0.221 in)

5.530 mm

(0.218 in)

5.152 mm

(0.203 in)

5.113 mm

(0.201 in)

5.190 mm

(0.204 in)

5.130 mm

(0.202 in)

NOTE:

HEAD ON THE HIDDEN SIDE F

01 PROTECT THE FASTENERS WITH MATERIAL No 06ABA1

OR

ASNA2019Ü56Ü25

01

FR45

TYPICAL SECTION

STGR36

STGR37

STGR38

STGR39

STGR40

A A

FR45 A

A

A

A

A

A

A

G A

(5)

(3)

(4)

(19)

90

47

9

92

F

F

D_SB_536177_5_VAAA_06_00

Figure A-FVAAA - Sheet 06

Removal/Installation of the Fasteners from FR41 to FR46, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 669

5

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

SERVICE BULLETIN

**CONF 001 thru 003

A

A

RH SHOWN

LH SYMMETRICAL

STRINGER DATUM

HOLE

SYMBOL ITEM PART NUMBER DESCRIPTION

HOLE DIAMETER

MIN MAX

RIVET

ASNA2529Ü3

 EN6114V3X6

NUT

SCREW

5.630 mm

(0.221 in)

5.530 mm

(0.218 in)

5.152 mm

(0.203 in)

5.113 mm

(0.201 in)

NOTE:

HEAD ON THE HIDDEN SIDE F

01 PROTECT THE FASTENERS WITH MATERIAL No 06ABA1

OR

ASNA2019Ü56Ü25

01

FR46

TYPICAL SECTION

STGR37

STGR38

STGR39

STGR40

A A

A

A

A

A

A

A

FR46

RIVET

ASNA2529Ü3

 EN6114V3X5

NUT

SCREW

5.630 mm

(0.221 in)

5.530 mm

(0.218 in)

5.152 mm

(0.203 in)

5.113 mm

(0.201 in)

OR

ASNA2019Ü56Ü25

(3)

(4)

91

9

EN6080D6XÜ32 RIVET 5.190 mm

(0.204 in)

5.130 mm

(0.202 in) (19) 92

(5)

(3)

(4)

(5)

90

47

9

90

F

F

F

H

D_SB_536177_5_VAAA_07_00

Figure A-FVAAA - Sheet 07

Removal/Installation of the Fasteners from FR41 to FR46, LH and RH Sides

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 670

5

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

SERVICE BULLETIN

**CONF 001 thru 003

SHEET 02 OR SHEET 03 

SEE FIG. AÜFFAAA

NOT INSPECTED AS PER

SERVICE BULLETIN A300Ü53Ü6111 OR

 NOT REPAIRED AS PER SERVICE BULLETIN

OR SHEET 04

YES NO

A300Ü53Ü6111 OR NOT REPAIRED

AS PER R53810329

FRAME FOOT PREVENTIVELY 

REPAIRED (NO CRACK) 

AS PER

YES NO

SERVICE BULLETIN 

A300Ü53Ü6111

FRAME FOOT REPAIRED IN AREA 1 

AS PER SERVICE BULLETIN 

A300Ü53Ü6111 OR R53810329

YES NO

SEE FIG. AÜFFAAA

SHEET 02

SEE FIG. AÜFFAAA

SHEET 03

SEE FIG. AÜFFAAA

SHEET 04

VERIFY THAT THE FRAME FOOT IS COVERED BY RDAS AND CONTACT 

AIRBUS WITHIN 6 MONTHS FOR FURTHER INSTRUCTIONS

DO A DETAILED INSPECTION OF THE FRAME FOOT AT FR41 ON LH SIDE (IN ACCORDANCE

INFORMATION PARAGRAPH E.(2) 

WITH TASK 536177Ü832Ü801Ü001) AT THE THRESHOLD GIVEN IN THE PLANNING

NOTE:

THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE

AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR

COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN

FRAME FOOT

D_SB_536177_5_FAAA_01_03

Figure A-FFAAA - Sheet 01

Flow Chart for Frame 41 on LH side

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 671

5

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

SERVICE BULLETIN

**CONF 001 thru 003

CRACK FOUND IN 

AREA 1 OR AREA 2 YES NO

DO A DETAILED INSPECTION OF THE AREA 1 AND THE AREA 2 OF THE FRAME FOOT

AT FR41 ON LH SIDE (IN ACCORDANCE WITH SUBTASK 536177Ü832Ü001Ü001)

SEE FIG. AÜFFAAA SHEET 01

CRACK HIGHER THAN 

30 mm (1.181 in) NO YES

AFFECTED FRAME FOOT FOR

 LABORATORY INVESTIGATIONS AND

INFORM AIRBUS, SEND THE

PERFORM THE FOLLOWING STEPS

OR

BEFORE NEXT FLIGHT

(IN ACCORDANCE WITH TASK 536177Ü833Ü801Ü001)

REPLACE THE CRACKED FRAME FOOT BY NEW ONE 

REPORT TO AIRBUS WITHIN 1 MONTH 

FROM INSPECTION DATE

REPEAT THE INSPECTION OF THE

REPLACED FRAME FOOT AT FR41

ON LH SIDE (IN ACCORDANCE WITH

TASK 536177Ü832Ü801Ü001) AT THE

THRESHOLD GIVEN IN THE PLANNING

INFORMATION PARAGRAPH E.(2) 02

01 THE ACCOMPLISHMENT OF THE SB 53Ü6176 REPLACES 

ALL FRAME FEET BETWEEN FR41 AND FR46

SEE FIG. AÜFFAAA SHEET 01

OR

APPLY SERVICE BULLETIN

A300Ü53Ü6176 BEFORE

NEXT FLIGHT 01

REPORT TO AIRBUS WITHIN 1 MONTH 

FROM INSPECTION DATE

REPEAT THE INSPECTION OF

THE FRAME FOOT AT FR41 ON

LH SIDE (IN ACCORDANCE WITH

TASK 536177Ü832Ü801Ü001) AT THE

INTERVAL GIVEN IN THE PLANNING

INFORMATION PARAGRAPH E.(2) 02

SEE FIG. AÜFFAAA SHEET 01

REPORT TO AIRBUS

WITHIN 1 MONTH FROM

INSPECTION DATE

NO FURTHER ACTION

NOTE:

THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE

AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR

COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN

02 REPEAT THE INSPECTION AT THE INTERVAL FOR NOT REPLACED FRAME

FOOT AND AT THE THRESHOLD FOR REPLACED FRAME FOOT

D_SB_536177_5_FAAA_02_02

Figure A-FFAAA - Sheet 02

Flow Chart for Frame 41 on LH side

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 672

5

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

SERVICE BULLETIN

**CONF 001 thru 003

CRACK FOUND IN 

AREA 1 OR AREA 2 YES NO

DO A DETAILED INSPECTION OF THE AREA 1 AND THE AREA 2 OF THE FRAME FOOT

AT FR41 ON LH SIDE (IN ACCORDANCE WITH SUBTASK 536177Ü832Ü001Ü001)

SEE FIG. AÜFFAAA SHEET 01

CRACK HIGHER THAN 

30 mm (1.181 in) NO YES

AFFECTED FRAME FOOT FOR

 LABORATORY INVESTIGATIONS AND

INFORM AIRBUS, SEND THE

PERFORM THE FOLLOWING STEPS

OR

AND DO THE CUTTINGÜOUT BEFORE NEXT FLIGHT

(IN ACCORDANCE WITH TASK 536177Ü833Ü801Ü001)

REPLACE THE CRACKED FRAME FOOT BY NEW ONE 

REPORT TO AIRBUS WITHIN 1 MONTH 

FROM INSPECTION DATE

REPEAT THE INSPECTION OF THE

REPLACED FRAME FOOT AT FR41

ON LH SIDE (IN ACCORDANCE WITH

TASK 536177Ü832Ü801Ü001) AT THE

THRESHOLD GIVEN IN THE PLANNING

INFORMATION PARAGRAPH E.(2) 02

01 THE ACCOMPLISHMENT OF THE SB 53Ü6176 REPLACES 

ALL FRAME FEET BETWEEN FR41 AND FR46

SEE FIG. AÜFFAAA SHEET 01

OR

APPLY SERVICE BULLETIN

A300Ü53Ü6176 BEFORE

NEXT FLIGHT 01

REPORT TO AIRBUS

WITHIN 1 MONTH FROM

INSPECTION DATE

NO FURTHER ACTION

NOTE:

THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE

AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR

COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN

02 REPEAT THE INSPECTION AT THE INTERVAL FOR NOT REPLACED FRAME

FOOT AND AT THE THRESHOLD FOR REPLACED FRAME FOOT

REPORT TO AIRBUS WITHIN 1 MONTH 

FROM INSPECTION DATE

REPEAT THE INSPECTION OF

THE FRAME FOOT AT FR41 ON

LH SIDE (IN ACCORDANCE WITH

TASK 536177Ü832Ü801Ü001) AT THE

INTERVAL GIVEN IN THE PLANNING

INFORMATION PARAGRAPH E.(2) 02

SEE FIG. AÜFFAAA SHEET 01

D_SB_536177_5_FAAA_03_02

Figure A-FFAAA - Sheet 03

Flow Chart for Frame 41 on LH side

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 673

5

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

SERVICE BULLETIN

**CONF 001 thru 003

CRACK FOUND IN 

AREA 2 YES NO

DO A DETAILED INSPECTION OF THE AREA 2 OF THE FRAME FOOT

AT FR41 ON LH SIDE (IN ACCORDANCE WITH SUBTASK 536177Ü832Ü001Ü001)

SEE FIG. AÜFFAAA SHEET 01

CRACK HIGHER THAN 

30 mm (1.181 in) NO YES

AFFECTED FRAME FOOT FOR

 LABORATORY INVESTIGATIONS AND

INFORM AIRBUS, SEND THE

PERFORM THE FOLLOWING STEPS

OR

AND DO THE CUTTINGÜOUT BEFORE NEXT FLIGHT

(IN ACCORDANCE WITH TASK 536177Ü833Ü801Ü001)

REPLACE THE CRACKED FRAME FOOT BY NEW ONE 

REPORT TO AIRBUS WITHIN 1 MONTH 

FROM INSPECTION DATE

REPEAT THE INSPECTION OF THE

REPLACED FRAME FOOT AT FR41

ON LH SIDE (IN ACCORDANCE WITH

TASK 536177Ü832Ü801Ü001) AT THE

THRESHOLD GIVEN IN THE PLANNING

INFORMATION PARAGRAPH E.(2) 02

01 THE ACCOMPLISHMENT OF THE SB 53Ü6176 REPLACES 

ALL FRAME FEET BETWEEN FR41 AND FR46

SEE FIG. AÜFFAAA SHEET 01

OR

APPLY SERVICE BULLETIN

A300Ü53Ü6176 BEFORE

NEXT FLIGHT 01

REPORT TO AIRBUS

WITHIN 1 MONTH FROM

INSPECTION DATE

NO FURTHER ACTION

NOTE:

THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE

AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR

COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN

02 REPEAT THE INSPECTION AT THE INTERVAL FOR NOT REPLACED FRAME

FOOT AND AT THE THRESHOLD FOR REPLACED FRAME FOOT

REPORT TO AIRBUS WITHIN 1 MONTH 

FROM INSPECTION DATE

REPEAT THE INSPECTION OF

THE FRAME FOOT AT FR41 ON

LH SIDE (IN ACCORDANCE WITH

TASK 536177Ü832Ü801Ü001) AT THE

INTERVAL GIVEN IN THE PLANNING

INFORMATION PARAGRAPH E.(2) 02

SEE FIG. AÜFFAAA SHEET 01

D_SB_536177_5_FAAA_04_02

Figure A-FFAAA - Sheet 04

Flow Chart for Frame 41 on LH side

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 674

5

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

SERVICE BULLETIN

**CONF 001 thru 003

SHEET 02 OR SHEET 03 

SEE FIG. AÜFFBAA

OR SHEET 04

YES NO

FRAME FOOT PREVENTIVELY 

REPAIRED (NO CRACK) 

AS PER

YES NO

SERVICE BULLETIN 

A300Ü53Ü6111

FRAME FOOT REPAIRED IN AREA 1 

AS PER SERVICE BULLETIN 

A300Ü53Ü6111 OR R53810329

YES NO

SEE FIG. AÜFFBAA

SHEET 02

SEE FIG. AÜFFBAA

SHEET 03

SEE FIG. AÜFFBAA

SHEET 04

VERIFY THAT THE FRAME FOOT IS COVERED BY RDAS AND CONTACT 

AIRBUS WITHIN 6 MONTHS FOR FURTHER INSTRUCTIONS

DO A DETAILED INSPECTION OF THE FRAME FOOT AT FR41 ON RH SIDE (IN ACCORDANCE

INFORMATION PARAGRAPH E.(2) 

WITH TASK 536177Ü832Ü801Ü001) AT THE THRESHOLD GIVEN IN THE PLANNING

NOTE:

THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE

AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR

COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN

NOT INSPECTED AS PER

SERVICE BULLETIN A300Ü53Ü6111 OR

 NOT REPAIRED AS PER SERVICE BULLETIN

A300Ü53Ü6111 OR NOT REPAIRED

AS PER R53810329

FRAME FOOT

D_SB_536177_5_FBAA_01_03

Figure A-FFBAA - Sheet 01

Flow Chart for Frame 41 on RH side

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 675

5

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

SERVICE BULLETIN

**CONF 001 thru 003

CRACK FOUND IN 

AREA 1 OR AREA 2 YES NO

DO A DETAILED INSPECTION OF THE AREA 1 AND THE AREA 2 OF THE FRAME FOOT

AT FR41 ON RH SIDE (IN ACCORDANCE WITH SUBTASK 536177Ü832Ü002Ü001)

SEE FIG. AÜFFBAA SHEET 01

CRACK HIGHER THAN 

30 mm (1.181 in) NO YES

AFFECTED FRAME FOOT FOR

 LABORATORY INVESTIGATIONS AND

INFORM AIRBUS, SEND THE

PERFORM THE FOLLOWING STEPS

OR

BEFORE NEXT FLIGHT

(IN ACCORDANCE WITH TASK 536177Ü833Ü801Ü001)

REPLACE THE CRACKED FRAME FOOT BY NEW ONE 

REPORT TO AIRBUS WITHIN 1 MONTH 

FROM INSPECTION DATE

REPEAT THE INSPECTION OF THE

REPLACED FRAME FOOT AT FR41

ON RH SIDE (IN ACCORDANCE WITH

TASK 536177Ü832Ü801Ü001) AT THE

THRESHOLD GIVEN IN THE PLANNING

INFORMATION PARAGRAPH E.(2) 02

01 THE ACCOMPLISHMENT OF THE SB 53Ü6176 REPLACES 

ALL FRAME FEET BETWEEN FR41 AND FR46

SEE FIG. AÜFFBAA SHEET 01

OR

APPLY SERVICE BULLETIN

A300Ü53Ü6176 BEFORE

NEXT FLIGHT 01

REPORT TO AIRBUS WITHIN 1 MONTH 

FROM INSPECTION DATE

REPEAT THE INSPECTION OF

THE FRAME FOOT AT FR41 ON

RH SIDE (IN ACCORDANCE WITH

TASK 536177Ü832Ü801Ü001) AT THE

INTERVAL GIVEN IN THE PLANNING

INFORMATION PARAGRAPH E.(2) 02

SEE FIG. AÜFFBAA SHEET 01

REPORT TO AIRBUS

WITHIN 1 MONTH FROM

INSPECTION DATE

NO FURTHER ACTION

NOTE:

THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE

AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR

COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN

02 REPEAT THE INSPECTION AT THE INTERVAL FOR NOT REPLACED FRAME

FOOT AND AT THE THRESHOLD FOR REPLACED FRAME FOOT

D_SB_536177_5_FBAA_02_02

Figure A-FFBAA - Sheet 02

Flow Chart for Frame 41 on RH side

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 676

5

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

SERVICE BULLETIN

**CONF 001 thru 003

CRACK FOUND IN 

AREA 1 OR AREA 2 YES NO

DO A DETAILED INSPECTION OF THE AREA 1 AND THE AREA 2 OF THE FRAME FOOT

AT FR41 ON RH SIDE (IN ACCORDANCE WITH SUBTASK 536177Ü832Ü002Ü001)

SEE FIG. AÜFFBAA SHEET 01

CRACK HIGHER THAN 

30 mm (1.181 in) NO YES

AFFECTED FRAME FOOT FOR

 LABORATORY INVESTIGATIONS AND

INFORM AIRBUS, SEND THE

PERFORM THE FOLLOWING STEPS

OR

AND DO THE CUTTINGÜOUT BEFORE NEXT FLIGHT

(IN ACCORDANCE WITH TASK 536177Ü833Ü801Ü001)

REPLACE THE CRACKED FRAME FOOT BY NEW ONE 

REPORT TO AIRBUS WITHIN 1 MONTH 

FROM INSPECTION DATE

REPEAT THE INSPECTION OF THE

REPLACED FRAME FOOT AT FR41

ON RH SIDE (IN ACCORDANCE WITH

TASK 536177Ü832Ü801Ü001) AT THE

THRESHOLD GIVEN IN THE PLANNING

INFORMATION PARAGRAPH E.(2) 02

01 THE ACCOMPLISHMENT OF THE SB 53Ü6176 REPLACES 

ALL FRAME FEET BETWEEN FR41 AND FR46

SEE FIG. AÜFFBAA SHEET 01

OR

APPLY SERVICE BULLETIN

A300Ü53Ü6176 BEFORE

NEXT FLIGHT 01

REPORT TO AIRBUS

WITHIN 1 MONTH FROM

INSPECTION DATE

NO FURTHER ACTION

NOTE:

THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE

AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR

COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN

02 REPEAT THE INSPECTION AT THE INTERVAL FOR NOT REPLACED FRAME

FOOT AND AT THE THRESHOLD FOR REPLACED FRAME FOOT

REPORT TO AIRBUS WITHIN 1 MONTH 

FROM INSPECTION DATE

REPEAT THE INSPECTION OF

THE FRAME FOOT AT FR41 ON

RH SIDE (IN ACCORDANCE WITH

TASK 536177Ü832Ü801Ü001) AT THE

INTERVAL GIVEN IN THE PLANNING

INFORMATION PARAGRAPH E.(2) 02

SEE FIG. AÜFFBAA SHEET 01

D_SB_536177_5_FBAA_03_02

Figure A-FFBAA - Sheet 03

Flow Chart for Frame 41 on RH side

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 677

5

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

SERVICE BULLETIN

**CONF 001 thru 003

CRACK FOUND IN 

AREA 2 YES NO

DO A DETAILED INSPECTION OF THE AREA 2 OF THE FRAME FOOT

AT FR41 ON RH SIDE (IN ACCORDANCE WITH SUBTASK 536177Ü832Ü002Ü001)

SEE FIG. AÜFFBAA SHEET 01

CRACK HIGHER THAN 

30 mm (1.181 in) NO YES

AFFECTED FRAME FOOT FOR

 LABORATORY INVESTIGATIONS AND

INFORM AIRBUS, SEND THE

PERFORM THE FOLLOWING STEPS

OR

AND DO THE CUTTINGÜOUT BEFORE NEXT FLIGHT

(IN ACCORDANCE WITH TASK 536177Ü833Ü801Ü001)

REPLACE THE CRACKED FRAME FOOT BY NEW ONE 

REPORT TO AIRBUS WITHIN 1 MONTH 

FROM INSPECTION DATE

REPEAT THE INSPECTION OF THE

REPLACED FRAME FOOT AT FR41

ON RH SIDE (IN ACCORDANCE WITH

TASK 536177Ü832Ü801Ü001) AT THE

THRESHOLD GIVEN IN THE PLANNING

INFORMATION PARAGRAPH E.(2) 02

01 THE ACCOMPLISHMENT OF THE SB 53Ü6176 REPLACES 

ALL FRAME FEET BETWEEN FR41 AND FR46

SEE FIG. AÜFFBAA SHEET 01

OR

APPLY SERVICE BULLETIN

A300Ü53Ü6176 BEFORE

NEXT FLIGHT 01

REPORT TO AIRBUS

WITHIN 1 MONTH FROM

INSPECTION DATE

NO FURTHER ACTION

NOTE:

THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE

AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR

COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN

02 REPEAT THE INSPECTION AT THE INTERVAL FOR NOT REPLACED FRAME

FOOT AND AT THE THRESHOLD FOR REPLACED FRAME FOOT

REPORT TO AIRBUS WITHIN 1 MONTH 

FROM INSPECTION DATE

REPEAT THE INSPECTION OF

THE FRAME FOOT AT FR41 ON

RH SIDE (IN ACCORDANCE WITH

TASK 536177Ü832Ü801Ü001) AT THE

INTERVAL GIVEN IN THE PLANNING

INFORMATION PARAGRAPH E.(2) 02

SEE FIG. AÜFFBAA SHEET 01

D_SB_536177_5_FBAA_04_02

Figure A-FFBAA - Sheet 04

Flow Chart for Frame 41 on RH side

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 678

5

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

SERVICE BULLETIN

**CONF 001 thru 003

SHEET 02 OR SHEET 03 

SEE FIG. AÜFFCAA

OR SHEET 04

YES NO

FRAME FOOT

PREVENTIVELY REPAIRED

YES (NO CRACK) AS PER NO

SERVICE BULLETIN 

A300Ü53Ü6111

FRAME FOOT REPAIRED IN AREA 1 

AS PER SERVICE BULLETIN 

A300Ü53Ü6111 OR R53810330

YES NO

SEE FIG. AÜFFCAA

SHEET 02

SEE FIG. AÜFFCAA

SHEET 03

SEE FIG. AÜFFCAA

SHEET 04

VERIFY THAT THE FRAME FOOT IS COVERED BY RDAS AND CONTACT

AIRBUS WITHIN 6 MONTHS FOR FURTHER INSTRUCTIONS

DO A DETAILED INSPECTION OF THE FRAME FOOT AT FR42 ON LH SIDE (IN ACCORDANCE

INFORMATION PARAGRAPH E.(2) 

WITH TASK 536177Ü832Ü801Ü001) AT THE THRESHOLD GIVEN IN THE PLANNING

NOTE:

THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE

AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR

COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN

NOT INSPECTED AS PER

SERVICE BULLETIN A300Ü53Ü6111 OR

 NOT REPAIRED AS PER SERVICE BULLETIN

A300Ü53Ü6111 OR NOT REPAIRED

AS PER R53810330

FRAME FOOT

D_SB_536177_5_FCAA_01_02

Figure A-FFCAA - Sheet 01

Flow Chart for Frame 42 on LH side

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 679

5

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

SERVICE BULLETIN

**CONF 001 thru 003

CRACK FOUND IN 

AREA 1 OR AREA 2 YES NO

DO A DETAILED INSPECTION OF THE AREA 1 AND THE AREA 2 OF THE FRAME FOOT

AT FR42 ON LH SIDE (IN ACCORDANCE WITH SUBTASK 536177Ü832Ü003Ü001)

SEE FIG. AÜFFCAA SHEET 01

CRACK HIGHER THAN 

30 mm (1.181 in) NO YES

AFFECTED FRAME FOOT FOR

 LABORATORY INVESTIGATIONS AND

INFORM AIRBUS, SEND THE

PERFORM THE FOLLOWING STEPS

OR

BEFORE NEXT FLIGHT

REPLACE THE CRACKED FRAME FOOT BY NEW ONE 

(IN ACCORDANCE WITH TASK 536177Ü833Ü801Ü001)

REPORT TO AIRBUS WITHIN 1 MONTH 

FROM INSPECTION DATE

REPEAT THE INSPECTION OF THE

REPLACED FRAME FOOT AT FR42

ON LH SIDE (IN ACCORDANCE WITH

TASK 536177Ü832Ü801Ü001) AT THE

THRESHOLD GIVEN IN THE PLANNING

INFORMATION PARAGRAPH E.(2) 02

01 THE ACCOMPLISHMENT OF THE SB 53Ü6176 REPLACES 

ALL FRAME FEET BETWEEN FR41 AND FR46

SEE FIG. AÜFFCAA SHEET 01

OR

APPLY SERVICE BULLETIN

A300Ü53Ü6176 BEFORE

NEXT FLIGHT 01

REPORT TO AIRBUS WITHIN 1 MONTH 

FROM INSPECTION DATE

REPEAT THE INSPECTION OF

THE FRAME FOOT AT FR42 ON

LH SIDE (IN ACCORDANCE WITH

TASK 536177Ü832Ü801Ü001) AT THE

INTERVAL GIVEN IN THE PLANNING

INFORMATION PARAGRAPH E.(2) 02

SEE FIG. AÜFFCAA SHEET 01

REPORT TO AIRBUS

WITHIN 1 MONTH FROM

INSPECTION DATE

NO FURTHER ACTION

NOTE:

THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE

AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR

COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN

02 REPEAT THE INSPECTION AT THE INTERVAL FOR NOT REPLACED FRAME

FOOT AND AT THE THRESHOLD FOR REPLACED FRAME FOOT

D_SB_536177_5_FCAA_02_01

Figure A-FFCAA - Sheet 02

Flow Chart for Frame 42 on LH side

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 680

5

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

SERVICE BULLETIN

**CONF 001 thru 003

CRACK FOUND IN 

AREA 1 OR AREA 2 YES NO

DO A DETAILED INSPECTION OF THE AREA 1 AND THE AREA 2 OF THE FRAME FOOT

AT FR42 ON LH SIDE (IN ACCORDANCE WITH SUBTASK 536177Ü832Ü003Ü001)

SEE FIG. AÜFFCAA SHEET 01

CRACK HIGHER THAN 

30 mm (1.181 in) NO YES

AFFECTED FRAME FOOT FOR

 LABORATORY INVESTIGATIONS AND

INFORM AIRBUS, SEND THE

PERFORM THE FOLLOWING STEPS

OR

AND DO THE CUTTINGÜOUT BEFORE NEXT FLIGHT

REPLACE THE CRACKED FRAME FOOT BY NEW ONE 

(IN ACCORDANCE WITH TASK 536177Ü833Ü801Ü001)

REPORT TO AIRBUS WITHIN 1 MONTH 

FROM INSPECTION DATE

REPEAT THE INSPECTION OF THE

REPLACED FRAME FOOT AT FR42

ON LH SIDE (IN ACCORDANCE WITH

TASK 536177Ü832Ü801Ü001) AT THE

THRESHOLD GIVEN IN THE PLANNING

INFORMATION PARAGRAPH E.(2) 02

01 THE ACCOMPLISHMENT OF THE SB 53Ü6176 REPLACES 

ALL FRAME FEET BETWEEN FR41 AND FR46

SEE FIG. AÜFFCAA SHEET 01

OR

APPLY SERVICE BULLETIN

A300Ü53Ü6176 BEFORE

NEXT FLIGHT 01

REPORT TO AIRBUS

WITHIN 1 MONTH FROM

INSPECTION DATE

NO FURTHER ACTION

NOTE:

THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE

AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR

COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN

02 REPEAT THE INSPECTION AT THE INTERVAL FOR NOT REPLACED FRAME

FOOT AND AT THE THRESHOLD FOR REPLACED FRAME FOOT

REPORT TO AIRBUS WITHIN 1 MONTH 

FROM INSPECTION DATE

REPEAT THE INSPECTION OF

THE FRAME FOOT AT FR42 ON

LH SIDE (IN ACCORDANCE WITH

TASK 536177Ü832Ü801Ü001) AT THE

INTERVAL GIVEN IN THE PLANNING

INFORMATION PARAGRAPH E.(2) 02

SEE FIG. AÜFFCAA SHEET 01

D_SB_536177_5_FCAA_03_01

Figure A-FFCAA - Sheet 03

Flow Chart for Frame 42 on LH side

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 681

5

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

SERVICE BULLETIN

**CONF 001 thru 003

CRACK FOUND IN 

AREA 2 YES NO

DO A DETAILED INSPECTION OF THE AREA 2 OF THE FRAME FOOT

AT FR42 ON LH SIDE (IN ACCORDANCE WITH SUBTASK 536177Ü832Ü003Ü001)

SEE FIG. AÜFFCAA SHEET 01

CRACK HIGHER THAN 

30 mm (1.181 in) NO YES

AFFECTED FRAME FOOT FOR

 LABORATORY INVESTIGATIONS AND

INFORM AIRBUS, SEND THE

PERFORM THE FOLLOWING STEPS

OR

AND DO THE CUTTINGÜOUT BEFORE NEXT FLIGHT

REPLACE THE CRACKED FRAME FOOT BY NEW ONE 

(IN ACCORDANCE WITH TASK 536177Ü833Ü801Ü001)

REPORT TO AIRBUS WITHIN 1 MONTH 

FROM INSPECTION DATE

REPEAT THE INSPECTION OF THE

REPLACED FRAME FOOT AT FR42

ON LH SIDE (IN ACCORDANCE WITH

TASK 536177Ü832Ü801Ü001) AT THE

THRESHOLD GIVEN IN THE PLANNING

INFORMATION PARAGRAPH E.(2) 02

01 THE ACCOMPLISHMENT OF THE SB 53Ü6176 REPLACES 

ALL FRAME FEET BETWEEN FR41 AND FR46

SEE FIG. AÜFFCAA SHEET 01

OR

APPLY SERVICE BULLETIN

A300Ü53Ü6176 BEFORE

NEXT FLIGHT 01

REPORT TO AIRBUS

WITHIN 1 MONTH FROM

INSPECTION DATE

NO FURTHER ACTION

NOTE:

THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE

AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR

COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN

02 REPEAT THE INSPECTION AT THE INTERVAL FOR NOT REPLACED FRAME

FOOT AND AT THE THRESHOLD FOR REPLACED FRAME FOOT

REPORT TO AIRBUS WITHIN 1 MONTH 

FROM INSPECTION DATE

REPEAT THE INSPECTION OF

THE FRAME FOOT AT FR42 ON

LH SIDE (IN ACCORDANCE WITH

TASK 536177Ü832Ü801Ü001) AT THE

INTERVAL GIVEN IN THE PLANNING

INFORMATION PARAGRAPH E.(2) 02

SEE FIG. AÜFFCAA SHEET 01

D_SB_536177_5_FCAA_04_01

Figure A-FFCAA - Sheet 04

Flow Chart for Frame 42 on LH side

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 682

5

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

SERVICE BULLETIN

**CONF 001 thru 003

SHEET 02 OR SHEET 03 

SEE FIG. AÜFFDAA

OR SHEET 04

YES NO

YES NO

YES NO

SEE FIG. AÜFFDAA

SHEET 02

SEE FIG. AÜFFDAA

SHEET 03

SEE FIG. AÜFFDAA

SHEET 04

VERIFY THAT THE FRAME FOOT IS COVERED BY RDAS AND CONTACT

AIRBUS WITHIN 6 MONTHS FOR FURTHER INSTRUCTIONS

DO A DETAILED INSPECTION OF THE FRAME FOOT AT FR42 ON RH SIDE (IN ACCORDANCE

INFORMATION PARAGRAPH E.(2) 

WITH TASK 536177Ü832Ü801Ü001) AT THE THRESHOLD GIVEN IN THE PLANNING

NOTE:

THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE

AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR

COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN

FRAME FOOT

PREVENTIVELY REPAIRED

(NO CRACK) AS PER

SERVICE BULLETIN 

A300Ü53Ü6111

FRAME FOOT REPAIRED IN AREA 1 

AS PER SERVICE BULLETIN 

A300Ü53Ü6111 OR R53810330

NOT INSPECTED AS PER

SERVICE BULLETIN A300Ü53Ü6111 OR

 NOT REPAIRED AS PER SERVICE BULLETIN

A300Ü53Ü6111 OR NOT REPAIRED

AS PER R53810330

FRAME FOOT

D_SB_536177_5_FDAA_01_02

Figure A-FFDAA - Sheet 01

Flow Chart for Frame 42 on RH side

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 683

5

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

SERVICE BULLETIN

**CONF 001 thru 003

CRACK FOUND IN 

AREA 1 OR AREA 2 YES NO

DO A DETAILED INSPECTION OF THE AREA 1 AND THE AREA 2 OF THE FRAME FOOT

AT FR42 ON RH SIDE (IN ACCORDANCE WITH SUBTASK 536177Ü832Ü004Ü001)

SEE FIG. AÜFFDAA SHEET 01

CRACK HIGHER THAN 

30 mm (1.181 in) NO YES

AFFECTED FRAME FOOT FOR

 LABORATORY INVESTIGATIONS AND

INFORM AIRBUS, SEND THE

PERFORM THE FOLLOWING STEPS

OR

BEFORE NEXT FLIGHT

REPLACE THE CRACKED FRAME FOOT BY NEW ONE 

(IN ACCORDANCE WITH TASK 536177Ü833Ü801Ü001)

REPORT TO AIRBUS WITHIN 1 MONTH 

FROM INSPECTION DATE

REPEAT THE INSPECTION OF THE

REPLACED FRAME FOOT AT FR42

ON RH SIDE (IN ACCORDANCE WITH

TASK 536177Ü832Ü801Ü001) AT THE

THRESHOLD GIVEN IN THE PLANNING

INFORMATION PARAGRAPH E.(2) 02

01 THE ACCOMPLISHMENT OF THE SB 53Ü6176 REPLACES 

ALL FRAME FEET BETWEEN FR41 AND FR46

SEE FIG. AÜFFDAA SHEET 01

OR

APPLY SERVICE BULLETIN

A300Ü53Ü6176 BEFORE

NEXT FLIGHT 01

REPORT TO AIRBUS WITHIN 1 MONTH 

FROM INSPECTION DATE

REPEAT THE INSPECTION OF

THE FRAME FOOT AT FR42 ON

RH SIDE (IN ACCORDANCE WITH

TASK 536177Ü832Ü801Ü001) AT THE

INTERVAL GIVEN IN THE PLANNING

INFORMATION PARAGRAPH E.(2) 02

SEE FIG. AÜFFDAA SHEET 01

REPORT TO AIRBUS

WITHIN 1 MONTH FROM

INSPECTION DATE

NO FURTHER ACTION

NOTE:

THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE

AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR

COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN

02 REPEAT THE INSPECTION AT THE INTERVAL FOR NOT REPLACED FRAME

FOOT AND AT THE THRESHOLD FOR REPLACED FRAME FOOT

D_SB_536177_5_FDAA_02_01

Figure A-FFDAA - Sheet 02

Flow Chart for Frame 42 on RH side

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 684

5

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

SERVICE BULLETIN

**CONF 001 thru 003

CRACK FOUND IN 

AREA 1 OR AREA 2 YES NO

DO A DETAILED INSPECTION OF THE AREA 1 AND THE AREA 2 OF THE FRAME FOOT

AT FR42 ON RH SIDE (IN ACCORDANCE WITH SUBTASK 536177Ü832Ü004Ü001)

SEE FIG. AÜFFDAA SHEET 01

CRACK HIGHER THAN 

30 mm (1.181 in) NO YES

AFFECTED FRAME FOOT FOR

 LABORATORY INVESTIGATIONS AND

INFORM AIRBUS, SEND THE

PERFORM THE FOLLOWING STEPS

OR

AND DO THE CUTTINGÜOUT BEFORE NEXT FLIGHT

REPLACE THE CRACKED FRAME FOOT BY NEW ONE 

(IN ACCORDANCE WITH TASK 536177Ü833Ü801Ü001)

REPORT TO AIRBUS WITHIN 1 MONTH 

FROM INSPECTION DATE

REPEAT THE INSPECTION OF THE

REPLACED FRAME FOOT AT FR42

ON RH SIDE (IN ACCORDANCE WITH

TASK 536177Ü832Ü801Ü001) AT THE

THRESHOLD GIVEN IN THE PLANNING

INFORMATION PARAGRAPH E.(2) 02

01 THE ACCOMPLISHMENT OF THE SB 53Ü6176 REPLACES 

ALL FRAME FEET BETWEEN FR41 AND FR46

SEE FIG. AÜFFDAA SHEET 01

OR

APPLY SERVICE BULLETIN

A300Ü53Ü6176 BEFORE

NEXT FLIGHT 01

REPORT TO AIRBUS

WITHIN 1 MONTH FROM

INSPECTION DATE

NO FURTHER ACTION

NOTE:

THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE

AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR

COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN

02 REPEAT THE INSPECTION AT THE INTERVAL FOR NOT REPLACED FRAME

FOOT AND AT THE THRESHOLD FOR REPLACED FRAME FOOT

REPORT TO AIRBUS WITHIN 1 MONTH 

FROM INSPECTION DATE

REPEAT THE INSPECTION OF

THE FRAME FOOT AT FR42 ON

RH SIDE (IN ACCORDANCE WITH

TASK 536177Ü832Ü801Ü001) AT THE

INTERVAL GIVEN IN THE PLANNING

INFORMATION PARAGRAPH E.(2) 02

SEE FIG. AÜFFDAA SHEET 01

D_SB_536177_5_FDAA_03_01

Figure A-FFDAA - Sheet 03

Flow Chart for Frame 42 on RH side

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 685

5

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

SERVICE BULLETIN

**CONF 001 thru 003

CRACK FOUND IN 

AREA 2 YES NO

DO A DETAILED INSPECTION OF THE AREA 2 OF THE FRAME FOOT

AT FR42 ON RH SIDE (IN ACCORDANCE WITH SUBTASK 536177Ü832Ü004Ü001)

SEE FIG. AÜFFDAA SHEET 01

CRACK HIGHER THAN 

30 mm (1.181 in) NO YES

AFFECTED FRAME FOOT FOR

 LABORATORY INVESTIGATIONS AND

INFORM AIRBUS, SEND THE

PERFORM THE FOLLOWING STEPS

OR

AND DO THE CUTTINGÜOUT BEFORE NEXT FLIGHT

REPLACE THE CRACKED FRAME FOOT BY NEW ONE 

(IN ACCORDANCE WITH TASK 536177Ü833Ü801Ü001)

REPORT TO AIRBUS WITHIN 1 MONTH 

FROM INSPECTION DATE

REPEAT THE INSPECTION OF THE

REPLACED FRAME FOOT AT FR42

ON RH SIDE (IN ACCORDANCE WITH

TASK 536177Ü832Ü801Ü001) AT THE

THRESHOLD GIVEN IN THE PLANNING

INFORMATION PARAGRAPH E.(2) 02

01 THE ACCOMPLISHMENT OF THE SB 53Ü6176 REPLACES 

ALL FRAME FEET BETWEEN FR41 AND FR46

SEE FIG. AÜFFDAA SHEET 01

OR

APPLY SERVICE BULLETIN

A300Ü53Ü6176 BEFORE

NEXT FLIGHT 01

REPORT TO AIRBUS

WITHIN 1 MONTH FROM

INSPECTION DATE

NO FURTHER ACTION

NOTE:

THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE

AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR

COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN

02 REPEAT THE INSPECTION AT THE INTERVAL FOR NOT REPLACED FRAME

FOOT AND AT THE THRESHOLD FOR REPLACED FRAME FOOT

REPORT TO AIRBUS WITHIN 1 MONTH 

FROM INSPECTION DATE

REPEAT THE INSPECTION OF

THE FRAME FOOT AT FR42 ON

RH SIDE (IN ACCORDANCE WITH

TASK 536177Ü832Ü801Ü001) AT THE

INTERVAL GIVEN IN THE PLANNING

INFORMATION PARAGRAPH E.(2) 02

SEE FIG. AÜFFDAA SHEET 01

D_SB_536177_5_FDAA_04_01

Figure A-FFDAA - Sheet 04

Flow Chart for Frame 42 on RH side

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 686

5

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

SERVICE BULLETIN

**CONF 001 thru 003

SHEET 02 OR SHEET 03 

SEE FIG. AÜFFEAA

OR SHEET 04

YES NO

FRAME FOOT PREVENTIVELY 

REPAIRED (NO CRACK) 

AS PER

YES NO

SERVICE BULLETIN 

A300Ü53Ü6111

FRAME FOOT REPAIRED IN AREA 1 

AS PER SERVICE BULLETIN 

A300Ü53Ü6111 OR R53810331

YES NO

SEE FIG. AÜFFEAA

SHEET 02

SEE FIG. AÜFFEAA

SHEET 03

SEE FIG. AÜFFEAA

SHEET 04

VERIFY THAT THE FRAME FOOT IS COVERED BY RDAS AND CONTACT 

AIRBUS WITHIN 6 MONTHS FOR FURTHER INSTRUCTIONS

DO A DETAILED INSPECTION OF THE FRAME FOOT AT FR43 ON LH SIDE (IN ACCORDANCE

INFORMATION PARAGRAPH E.(2) 

WITH TASK 536177Ü832Ü801Ü001) AT THE THRESHOLD GIVEN IN THE PLANNING

NOTE:

THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE

AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR

COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN

NOT INSPECTED AS PER

SERVICE BULLETIN A300Ü53Ü6111 OR

 NOT REPAIRED AS PER SERVICE BULLETIN

A300Ü53Ü6111 OR NOT REPAIRED

AS PER R53810331

FRAME FOOT

D_SB_536177_5_FEAA_01_02

Figure A-FFEAA - Sheet 01

Flow Chart for Frame 43 on LH side

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 687

5

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

SERVICE BULLETIN

**CONF 001 thru 003

CRACK FOUND IN 

AREA 1 OR AREA 2 YES NO

DO A DETAILED INSPECTION OF THE AREA 1 AND THE AREA 2 OF THE FRAME FOOT

AT FR43 ON LH SIDE (IN ACCORDANCE WITH SUBTASK 536177Ü832Ü005Ü001)

SEE FIG. AÜFFEAA SHEET 01

CRACK HIGHER THAN 

30 mm (1.181 in) NO YES

AFFECTED FRAME FOOT FOR

 LABORATORY INVESTIGATIONS AND

INFORM AIRBUS, SEND THE

PERFORM THE FOLLOWING STEPS

OR

BEFORE NEXT FLIGHT

(IN ACCORDANCE WITH TASK 536177Ü833Ü801Ü001)

REPLACE THE CRACKED FRAME FOOT BY NEW ONE 

REPORT TO AIRBUS WITHIN 1 MONTH 

FROM INSPECTION DATE

REPEAT THE INSPECTION OF THE

REPLACED FRAME FOOT AT FR43

ON LH SIDE (IN ACCORDANCE WITH

TASK 536177Ü832Ü801Ü001) AT THE

THRESHOLD GIVEN IN THE PLANNING

INFORMATION PARAGRAPH E.(2) 02

01 THE ACCOMPLISHMENT OF THE SB 53Ü6176 REPLACES 

ALL FRAME FEET BETWEEN FR41 AND FR46

SEE FIG. AÜFFEAA SHEET 01

OR

APPLY SERVICE BULLETIN

A300Ü53Ü6176 BEFORE

NEXT FLIGHT 01

REPORT TO AIRBUS WITHIN 1 MONTH 

FROM INSPECTION DATE

REPEAT THE INSPECTION OF

THE FRAME FOOT AT FR43 ON

LH SIDE (IN ACCORDANCE WITH

TASK 536177Ü832Ü801Ü001) AT THE

INTERVAL GIVEN IN THE PLANNING

INFORMATION PARAGRAPH E.(2) 02

SEE FIG. AÜFFEAA SHEET 01

REPORT TO AIRBUS

WITHIN 1 MONTH FROM

INSPECTION DATE

NO FURTHER ACTION

NOTE:

THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE

AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR

COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN

02 REPEAT THE INSPECTION AT THE INTERVAL FOR NOT REPLACED FRAME

FOOT AND AT THE THRESHOLD FOR REPLACED FRAME FOOT

D_SB_536177_5_FEAA_02_01

Figure A-FFEAA - Sheet 02

Flow Chart for Frame 43 on LH side

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 688

5

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

SERVICE BULLETIN

**CONF 001 thru 003

CRACK FOUND IN 

AREA 1 OR AREA 2 YES NO

DO A DETAILED INSPECTION OF THE AREA 1 AND THE AREA 2 OF THE FRAME FOOT

AT FR43 ON LH SIDE (IN ACCORDANCE WITH SUBTASK 536177Ü832Ü005Ü001)

SEE FIG. AÜFFEAA SHEET 01

CRACK HIGHER THAN 

30 mm (1.181 in) NO YES

AFFECTED FRAME FOOT FOR

 LABORATORY INVESTIGATIONS AND

INFORM AIRBUS, SEND THE

PERFORM THE FOLLOWING STEPS

OR

AND DO THE CUTTINGÜOUT BEFORE NEXT FLIGHT

(IN ACCORDANCE WITH TASK 536177Ü833Ü801Ü001)

REPLACE THE CRACKED FRAME FOOT BY NEW ONE 

REPORT TO AIRBUS WITHIN 1 MONTH 

FROM INSPECTION DATE

REPEAT THE INSPECTION OF THE

REPLACED FRAME FOOT AT FR43

ON LH SIDE (IN ACCORDANCE WITH

TASK 536177Ü832Ü801Ü001) AT THE

THRESHOLD GIVEN IN THE PLANNING

INFORMATION PARAGRAPH E.(2) 02

01 THE ACCOMPLISHMENT OF THE SB 53Ü6176 REPLACES 

ALL FRAME FEET BETWEEN FR41 AND FR46

SEE FIG. AÜFFEAA SHEET 01

OR

APPLY SERVICE BULLETIN

A300Ü53Ü6176 BEFORE

NEXT FLIGHT 01

REPORT TO AIRBUS

WITHIN 1 MONTH FROM

INSPECTION DATE

NO FURTHER ACTION

NOTE:

THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE

AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR

COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN

02 REPEAT THE INSPECTION AT THE INTERVAL FOR NOT REPLACED FRAME

FOOT AND AT THE THRESHOLD FOR REPLACED FRAME FOOT

REPORT TO AIRBUS WITHIN 1 MONTH 

FROM INSPECTION DATE

REPEAT THE INSPECTION OF

THE FRAME FOOT AT FR43 ON

LH SIDE (IN ACCORDANCE WITH

TASK 536177Ü832Ü801Ü001) AT THE

INTERVAL GIVEN IN THE PLANNING

INFORMATION PARAGRAPH E.(2) 02

SEE FIG. AÜFFEAA SHEET 01

D_SB_536177_5_FEAA_03_01

Figure A-FFEAA - Sheet 03

Flow Chart for Frame 43 on LH side

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 689

5

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

SERVICE BULLETIN

**CONF 001 thru 003

CRACK FOUND IN 

AREA 2 YES NO

DO A DETAILED INSPECTION OF THE AREA 2 OF THE FRAME FOOT

AT FR43 ON LH SIDE (IN ACCORDANCE WITH SUBTASK 536177Ü832Ü005Ü001)

SEE FIG. AÜFFEAA SHEET 01

CRACK HIGHER THAN 

30 mm (1.181 in) NO YES

AFFECTED FRAME FOOT FOR

 LABORATORY INVESTIGATIONS AND

INFORM AIRBUS, SEND THE

PERFORM THE FOLLOWING STEPS

OR

AND DO THE CUTTINGÜOUT BEFORE NEXT FLIGHT

REPLACE THE CRACKED FRAME FOOT BY NEW ONE 

(IN ACCORDANCE WITH TASK 536177Ü833Ü801Ü001)

REPORT TO AIRBUS WITHIN 1 MONTH 

FROM INSPECTION DATE

REPEAT THE INSPECTION OF THE

REPLACED FRAME FOOT AT FR43

ON LH SIDE (IN ACCORDANCE WITH

TASK 536177Ü832Ü801Ü001) AT THE

THRESHOLD GIVEN IN THE PLANNING

INFORMATION PARAGRAPH E.(2) 02

01 THE ACCOMPLISHMENT OF THE SB 53Ü6176 REPLACES 

ALL FRAME FEET BETWEEN FR41 AND FR46

SEE FIG. AÜFFEAA SHEET 01

OR

APPLY SERVICE BULLETIN

A300Ü53Ü6176 BEFORE

NEXT FLIGHT 01

REPORT TO AIRBUS

WITHIN 1 MONTH FROM

INSPECTION DATE

NO FURTHER ACTION

NOTE:

THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE

AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR

COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN

02 REPEAT THE INSPECTION AT THE INTERVAL FOR NOT REPLACED FRAME

FOOT AND AT THE THRESHOLD FOR REPLACED FRAME FOOT

REPORT TO AIRBUS WITHIN 1 MONTH 

FROM INSPECTION DATE

REPEAT THE INSPECTION OF

THE FRAME FOOT AT FR43 ON

LH SIDE (IN ACCORDANCE WITH

TASK 536177Ü832Ü801Ü001) AT THE

INTERVAL GIVEN IN THE PLANNING

INFORMATION PARAGRAPH E.(2) 02

SEE FIG. AÜFFEAA SHEET 01

D_SB_536177_5_FEAA_04_01

Figure A-FFEAA - Sheet 04

Flow Chart for Frame 43 on LH side

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 690

5

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

SERVICE BULLETIN

**CONF 001 thru 003

SHEET 02 OR SHEET 03 

SEE FIG. AÜFFFAA

OR SHEET 04

YES NO

FRAME FOOT PREVENTIVELY 

REPAIRED (NO CRACK) 

AS PER

YES NO

SERVICE BULLETIN 

A300Ü53Ü6111

FRAME FOOT REPAIRED IN AREA 1 

AS PER SERVICE BULLETIN 

A300Ü53Ü6111 OR R53810331

YES NO

SEE FIG. AÜFFFAA

SHEET 02

SEE FIG. AÜFFFAA

SHEET 03

SEE FIG. AÜFFFAA

SHEET 04

VERIFY THAT THE FRAME FOOT IS COVERED BY RDAS AND CONTACT 

AIRBUS WITHIN 6 MONTHS FOR FURTHER INSTRUCTIONS

DO A DETAILED INSPECTION OF THE FRAME FOOT AT FR43 ON RH SIDE (IN ACCORDANCE

INFORMATION PARAGRAPH E.(2) 

WITH TASK 536177Ü832Ü801Ü001) AT THE THRESHOLD GIVEN IN THE PLANNING

NOTE:

THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE

AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR

COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN

NOT INSPECTED AS PER

SERVICE BULLETIN A300Ü53Ü6111 OR

 NOT REPAIRED AS PER SERVICE BULLETIN

A300Ü53Ü6111 OR NOT REPAIRED

AS PER R53810331

FRAME FOOT

D_SB_536177_5_FFAA_01_02

Figure A-FFFAA - Sheet 01

Flow Chart for Frame 43 on RH side

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 691

5

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

SERVICE BULLETIN

**CONF 001 thru 003

CRACK FOUND IN 

AREA 1 OR AREA 2 YES NO

DO A DETAILED INSPECTION OF THE AREA 1 AND THE AREA 2 OF THE FRAME FOOT

AT FR43 ON RH SIDE (IN ACCORDANCE WITH SUBTASK 536177Ü832Ü006Ü001)

SEE FIG. AÜFFFAA SHEET 01

CRACK HIGHER THAN 

30 mm (1.181 in) NO YES

AFFECTED FRAME FOOT FOR

 LABORATORY INVESTIGATIONS AND

INFORM AIRBUS, SEND THE

PERFORM THE FOLLOWING STEPS

OR

BEFORE NEXT FLIGHT

(IN ACCORDANCE WITH TASK 536177Ü833Ü801Ü001)

REPLACE THE CRACKED FRAME FOOT BY NEW ONE 

REPORT TO AIRBUS WITHIN 1 MONTH 

FROM INSPECTION DATE

REPEAT THE INSPECTION OF THE

REPLACED FRAME FOOT AT FR43

ON RH SIDE (IN ACCORDANCE WITH

TASK 536177Ü832Ü801Ü001) AT THE

THRESHOLD GIVEN IN THE PLANNING

INFORMATION PARAGRAPH E.(2) 02

01 THE ACCOMPLISHMENT OF THE SB 53Ü6176 REPLACES 

ALL FRAME FEET BETWEEN FR41 AND FR46

SEE FIG. AÜFFFAA SHEET 01

OR

APPLY SERVICE BULLETIN

A300Ü53Ü6176 BEFORE

NEXT FLIGHT 01

REPORT TO AIRBUS WITHIN 1 MONTH 

FROM INSPECTION DATE

REPEAT THE INSPECTION OF

THE FRAME FOOT AT FR43 ON

RH SIDE (IN ACCORDANCE WITH

TASK 536177Ü832Ü801Ü001) AT THE

INTERVAL GIVEN IN THE PLANNING

INFORMATION PARAGRAPH E.(2) 02

SEE FIG. AÜFFFAA SHEET 01

REPORT TO AIRBUS

WITHIN 1 MONTH FROM

INSPECTION DATE

NO FURTHER ACTION

NOTE:

THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE

AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR

COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN

02 REPEAT THE INSPECTION AT THE INTERVAL FOR NOT REPLACED FRAME

FOOT AND AT THE THRESHOLD FOR REPLACED FRAME FOOT

D_SB_536177_5_FFAA_02_01

Figure A-FFFAA - Sheet 02

Flow Chart for Frame 43 on RH side

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 692

5

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

SERVICE BULLETIN

**CONF 001 thru 003

CRACK FOUND IN 

AREA 1 OR AREA 2 YES NO

DO A DETAILED INSPECTION OF THE AREA 1 AND THE AREA 2 OF THE FRAME FOOT

AT FR43 ON RH SIDE (IN ACCORDANCE WITH SUBTASK 536177Ü832Ü006Ü001)

SEE FIG. AÜFFFAA SHEET 01

CRACK HIGHER THAN 

30 mm (1.181 in) NO YES

AFFECTED FRAME FOOT FOR

 LABORATORY INVESTIGATIONS AND

INFORM AIRBUS, SEND THE

PERFORM THE FOLLOWING STEPS

OR

AND DO THE CUTTINGÜOUT BEFORE NEXT FLIGHT

(IN ACCORDANCE WITH TASK 536177Ü833Ü801Ü001)

REPLACE THE CRACKED FRAME FOOT BY NEW ONE 

REPORT TO AIRBUS WITHIN 1 MONTH 

FROM INSPECTION DATE

REPEAT THE INSPECTION OF THE

REPLACED FRAME FOOT AT FR43

ON RH SIDE (IN ACCORDANCE WITH

TASK 536177Ü832Ü801Ü001) AT THE

THRESHOLD GIVEN IN THE PLANNING

INFORMATION PARAGRAPH E.(2) 02

01 THE ACCOMPLISHMENT OF THE SB 53Ü6176 REPLACES 

ALL FRAME FEET BETWEEN FR41 AND FR46

SEE FIG. AÜFFFAA SHEET 01

OR

APPLY SERVICE BULLETIN

A300Ü53Ü6176 BEFORE

NEXT FLIGHT 01

REPORT TO AIRBUS

WITHIN 1 MONTH FROM

INSPECTION DATE

NO FURTHER ACTION

NOTE:

THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE

AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR

COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN

02 REPEAT THE INSPECTION AT THE INTERVAL FOR NOT REPLACED FRAME

FOOT AND AT THE THRESHOLD FOR REPLACED FRAME FOOT

REPORT TO AIRBUS WITHIN 1 MONTH 

FROM INSPECTION DATE

REPEAT THE INSPECTION OF

THE FRAME FOOT AT FR43 ON

RH SIDE (IN ACCORDANCE WITH

TASK 536177Ü832Ü801Ü001) AT THE

INTERVAL GIVEN IN THE PLANNING

INFORMATION PARAGRAPH E.(2) 02

SEE FIG. AÜFFFAA SHEET 01

D_SB_536177_5_FFAA_03_01

Figure A-FFFAA - Sheet 03

Flow Chart for Frame 43 on RH side

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 693

5

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

SERVICE BULLETIN

**CONF 001 thru 003

CRACK FOUND IN 

AREA 2 YES NO

DO A DETAILED INSPECTION OF THE AREA 2 OF THE FRAME FOOT

AT FR43 ON RH SIDE (IN ACCORDANCE WITH SUBTASK 536177Ü832Ü006Ü001)

SEE FIG. AÜFFFAA SHEET 01

CRACK HIGHER THAN 

30 mm (1.181 in) NO YES

AFFECTED FRAME FOOT FOR

 LABORATORY INVESTIGATIONS AND

INFORM AIRBUS, SEND THE

PERFORM THE FOLLOWING STEPS

OR

AND DO THE CUTTINGÜOUT BEFORE NEXT FLIGHT

(IN ACCORDANCE WITH TASK 536177Ü833Ü801Ü001)

REPLACE THE CRACKED FRAME FOOT BY NEW ONE 

REPORT TO AIRBUS WITHIN 1 MONTH 

FROM INSPECTION DATE

REPEAT THE INSPECTION OF THE

REPLACED FRAME FOOT AT FR43

ON RH SIDE (IN ACCORDANCE WITH

TASK 536177Ü832Ü801Ü001) AT THE

THRESHOLD GIVEN IN THE PLANNING

INFORMATION PARAGRAPH E.(2) 02

01 THE ACCOMPLISHMENT OF THE SB 53Ü6176 REPLACES 

ALL FRAME FEET BETWEEN FR41 AND FR46

SEE FIG. AÜFFFAA SHEET 01

OR

APPLY SERVICE BULLETIN

A300Ü53Ü6176 BEFORE

NEXT FLIGHT 01

REPORT TO AIRBUS

WITHIN 1 MONTH FROM

INSPECTION DATE

NO FURTHER ACTION

NOTE:

THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE

AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR

COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN

02 REPEAT THE INSPECTION AT THE INTERVAL FOR NOT REPLACED FRAME

FOOT AND AT THE THRESHOLD FOR REPLACED FRAME FOOT

REPORT TO AIRBUS WITHIN 1 MONTH 

FROM INSPECTION DATE

REPEAT THE INSPECTION OF

THE FRAME FOOT AT FR43 ON

RH SIDE (IN ACCORDANCE WITH

TASK 536177Ü832Ü801Ü001) AT THE

INTERVAL GIVEN IN THE PLANNING

INFORMATION PARAGRAPH E.(2) 02

SEE FIG. AÜFFFAA SHEET 01

D_SB_536177_5_FFAA_04_01

Figure A-FFFAA - Sheet 04

Flow Chart for Frame 43 on RH side

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 694

5

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

SERVICE BULLETIN

**CONF 001 thru 003

SHEET 02 OR SHEET 03 

SEE FIG. AÜFFGAA

OR SHEET 04

YES NO

FRAME FOOT PREVENTIVELY 

REPAIRED (NO CRACK) 

AS PER

YES NO

SERVICE BULLETIN 

A300Ü53Ü6111

FRAME FOOT REPAIRED IN AREA 1 

AS PER SERVICE BULLETIN 

A300Ü53Ü6111 OR R53810332

YES NO

SEE FIG. AÜFFGAA

SHEET 02

SEE FIG. AÜFFGAA

SHEET 03

SEE FIG. AÜFFGAA

SHEET 04

VERIFY THAT THE FRAME FOOT IS COVERED BY RDAS AND CONTACT 

AIRBUS WITHIN 6 MONTHS FOR FURTHER INSTRUCTIONS

DO A DETAILED INSPECTION OF THE FRAME FOOT AT FR44 ON LH SIDE (IN ACCORDANCE

INFORMATION PARAGRAPH E.(2) 

WITH TASK 536177Ü832Ü801Ü001) AT THE THRESHOLD GIVEN IN THE PLANNING

NOTE:

THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE

AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR

COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN

NOT INSPECTED AS PER

SERVICE BULLETIN A300Ü53Ü6111 OR

 NOT REPAIRED AS PER SERVICE BULLETIN

A300Ü53Ü6111 OR NOT REPAIRED

AS PER R53810332

FRAME FOOT

D_SB_536177_5_FGAA_01_02

Figure A-FFGAA - Sheet 01

Flow Chart for Frame 44 on LH side

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 695

5

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

SERVICE BULLETIN

**CONF 001 thru 003

CRACK FOUND IN 

AREA 1 OR AREA 2 YES NO

DO A DETAILED INSPECTION OF THE AREA 1 AND THE AREA 2 OF THE FRAME FOOT

AT FR44 ON LH SIDE (IN ACCORDANCE WITH SUBTASK 536177Ü832Ü007Ü001)

SEE FIG. AÜFFGAA SHEET 01

CRACK HIGHER THAN 

30 mm (1.181 in) NO YES

AFFECTED FRAME FOOT FOR

 LABORATORY INVESTIGATIONS AND

INFORM AIRBUS, SEND THE

PERFORM THE FOLLOWING STEPS

OR

BEFORE NEXT FLIGHT

REPLACE THE CRACKED FRAME FOOT BY NEW ONE 

(IN ACCORDANCE WITH TASK 536177Ü833Ü801Ü001)

REPORT TO AIRBUS WITHIN 1 MONTH 

FROM INSPECTION DATE

REPEAT THE INSPECTION OF THE

REPLACED FRAME FOOT AT FR44

ON LH SIDE (IN ACCORDANCE WITH

TASK 536177Ü832Ü801Ü001) AT THE

THRESHOLD GIVEN IN THE PLANNING

INFORMATION PARAGRAPH E.(2) 02

01 THE ACCOMPLISHMENT OF THE SB 53Ü6176 REPLACES 

ALL FRAME FEET BETWEEN FR41 AND FR46

SEE FIG. AÜFFGAA SHEET 01

OR

APPLY SERVICE BULLETIN

A300Ü53Ü6176 BEFORE

NEXT FLIGHT 01

REPORT TO AIRBUS WITHIN 1 MONTH 

FROM INSPECTION DATE

REPEAT THE INSPECTION OF

THE FRAME FOOT AT FR44 ON

LH SIDE (IN ACCORDANCE WITH

TASK 536177Ü832Ü801Ü001) AT THE

INTERVAL GIVEN IN THE PLANNING

INFORMATION PARAGRAPH E.(2) 02

SEE FIG. AÜFFGAA SHEET 01

REPORT TO AIRBUS

WITHIN 1 MONTH FROM

INSPECTION DATE

NO FURTHER ACTION

NOTE:

THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE

AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR

COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN

02 REPEAT THE INSPECTION AT THE INTERVAL FOR NOT REPLACED FRAME

FOOT AND AT THE THRESHOLD FOR REPLACED FRAME FOOT

D_SB_536177_5_FGAA_02_01

Figure A-FFGAA - Sheet 02

Flow Chart for Frame 44 on LH side

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 696

5

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

SERVICE BULLETIN

**CONF 001 thru 003

CRACK FOUND IN 

AREA 1 OR AREA 2 YES NO

DO A DETAILED INSPECTION OF THE AREA 1 AND THE AREA 2 OF THE FRAME FOOT

AT FR44 ON LH SIDE (IN ACCORDANCE WITH SUBTASK 536177Ü832Ü007Ü001)

SEE FIG. AÜFFGAA SHEET 01

CRACK HIGHER THAN 

30 mm (1.181 in) NO YES

AFFECTED FRAME FOOT FOR

 LABORATORY INVESTIGATIONS AND

INFORM AIRBUS, SEND THE

PERFORM THE FOLLOWING STEPS

OR

AND DO THE CUTTINGÜOUT BEFORE NEXT FLIGHT

REPLACE THE CRACKED FRAME FOOT BY NEW ONE 

(IN ACCORDANCE WITH TASK 536177Ü833Ü801Ü001)

REPORT TO AIRBUS WITHIN 1 MONTH 

FROM INSPECTION DATE

REPEAT THE INSPECTION OF THE

REPLACED FRAME FOOT AT FR44

ON LH SIDE (IN ACCORDANCE WITH

TASK 536177Ü832Ü801Ü001) AT THE

THRESHOLD GIVEN IN THE PLANNING

INFORMATION PARAGRAPH E.(2) 02

01 THE ACCOMPLISHMENT OF THE SB 53Ü6176 REPLACES 

ALL FRAME FEET BETWEEN FR41 AND FR46

SEE FIG. AÜFFGAA SHEET 01

OR

APPLY SERVICE BULLETIN

A300Ü53Ü6176 BEFORE

NEXT FLIGHT 01

REPORT TO AIRBUS

WITHIN 1 MONTH FROM

INSPECTION DATE

NO FURTHER ACTION

NOTE:

THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE

AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR

COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN

02 REPEAT THE INSPECTION AT THE INTERVAL FOR NOT REPLACED FRAME

FOOT AND AT THE THRESHOLD FOR REPLACED FRAME FOOT

REPORT TO AIRBUS WITHIN 1 MONTH 

FROM INSPECTION DATE

REPEAT THE INSPECTION OF

THE FRAME FOOT AT FR44 ON

LH SIDE (IN ACCORDANCE WITH

TASK 536177Ü832Ü801Ü001) AT THE

INTERVAL GIVEN IN THE PLANNING

INFORMATION PARAGRAPH E.(2) 02

SEE FIG. AÜFFGAA SHEET 01

D_SB_536177_5_FGAA_03_01

Figure A-FFGAA - Sheet 03

Flow Chart for Frame 44 on LH side

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 697

5

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

SERVICE BULLETIN

**CONF 001 thru 003

CRACK FOUND IN 

AREA 2 YES NO

DO A DETAILED INSPECTION OF THE AREA 2 OF THE FRAME FOOT

AT FR44 ON LH SIDE (IN ACCORDANCE WITH SUBTASK 536177Ü832Ü007Ü001)

SEE FIG. AÜFFGAA SHEET 01

CRACK HIGHER THAN 

30 mm (1.181 in) NO YES

AFFECTED FRAME FOOT FOR

 LABORATORY INVESTIGATIONS AND

INFORM AIRBUS, SEND THE

PERFORM THE FOLLOWING STEPS

OR

AND DO THE CUTTINGÜOUT BEFORE NEXT FLIGHT

REPLACE THE CRACKED FRAME FOOT BY NEW ONE 

(IN ACCORDANCE WITH TASK 536177Ü833Ü801Ü001)

REPORT TO AIRBUS WITHIN 1 MONTH 

FROM INSPECTION DATE

REPEAT THE INSPECTION OF THE

REPLACED FRAME FOOT AT FR44

ON LH SIDE (IN ACCORDANCE WITH

TASK 536177Ü832Ü801Ü001) AT THE

THRESHOLD GIVEN IN THE PLANNING

INFORMATION PARAGRAPH E.(2) 02

01 THE ACCOMPLISHMENT OF THE SB 53Ü6176 REPLACES 

ALL FRAME FEET BETWEEN FR41 AND FR46

SEE FIG. AÜFFGAA SHEET 01

OR

APPLY SERVICE BULLETIN

A300Ü53Ü6176 BEFORE

NEXT FLIGHT 01

REPORT TO AIRBUS

WITHIN 1 MONTH FROM

INSPECTION DATE

NO FURTHER ACTION

NOTE:

THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE

AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR

COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN

02 REPEAT THE INSPECTION AT THE INTERVAL FOR NOT REPLACED FRAME

FOOT AND AT THE THRESHOLD FOR REPLACED FRAME FOOT

REPORT TO AIRBUS WITHIN 1 MONTH 

FROM INSPECTION DATE

REPEAT THE INSPECTION OF

THE FRAME FOOT AT FR44 ON

LH SIDE (IN ACCORDANCE WITH

TASK 536177Ü832Ü801Ü001) AT THE

INTERVAL GIVEN IN THE PLANNING

INFORMATION PARAGRAPH E.(2) 02

SEE FIG. AÜFFGAA SHEET 01

D_SB_536177_5_FGAA_04_01

Figure A-FFGAA - Sheet 04

Flow Chart for Frame 44 on LH side

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 698

5

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

SERVICE BULLETIN

**CONF 001 thru 003

SHEET 02 OR SHEET 03 

SEE FIG. AÜFFHAA

OR SHEET 04

YES NO

FRAME FOOT PREVENTIVELY 

REPAIRED (NO CRACK) 

AS PER

YES NO

SERVICE BULLETIN 

A300Ü53Ü6111

FRAME FOOT REPAIRED IN AREA 1 

AS PER SERVICE BULLETIN 

A300Ü53Ü6111 OR R53810332

YES NO

SEE FIG. AÜFFHAA

SHEET 02

SEE FIG. AÜFFHAA

SHEET 03

SEE FIG. AÜFFHAA

SHEET 04

VERIFY THAT THE FRAME FOOT IS COVERED BY RDAS AND CONTACT 

AIRBUS WITHIN 6 MONTHS FOR FURTHER INSTRUCTIONS

DO A DETAILED INSPECTION OF THE FRAME FOOT AT FR44 ON RH SIDE (IN ACCORDANCE

INFORMATION PARAGRAPH E.(2) 

WITH TASK 536177Ü832Ü801Ü001) AT THE THRESHOLD GIVEN IN THE PLANNING

NOTE:

THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE

AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR

COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN

NOT INSPECTED AS PER

SERVICE BULLETIN A300Ü53Ü6111 OR

 NOT REPAIRED AS PER SERVICE BULLETIN

A300Ü53Ü6111 OR NOT REPAIRED

AS PER R53810332

FRAME FOOT

D_SB_536177_5_FHAA_01_02

Figure A-FFHAA - Sheet 01

Flow Chart for Frame 44 on RH side

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 699

5

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

SERVICE BULLETIN

**CONF 001 thru 003

CRACK FOUND IN 

AREA 1 OR AREA 2 YES NO

DO A DETAILED INSPECTION OF THE AREA 1 AND THE AREA 2 OF THE FRAME FOOT

AT FR44 ON RH SIDE (IN ACCORDANCE WITH SUBTASK 536177Ü832Ü008Ü001)

SEE FIG. AÜFFHAA SHEET 01

CRACK HIGHER THAN 

30 mm (1.181 in) NO YES

AFFECTED FRAME FOOT FOR

 LABORATORY INVESTIGATIONS AND

INFORM AIRBUS, SEND THE

PERFORM THE FOLLOWING STEPS

OR

BEFORE NEXT FLIGHT

REPLACE THE CRACKED FRAME FOOT BY NEW ONE 

(IN ACCORDANCE WITH TASK 536177Ü833Ü801Ü001)

REPORT TO AIRBUS WITHIN 1 MONTH 

FROM INSPECTION DATE

REPEAT THE INSPECTION OF THE

REPLACED FRAME FOOT AT FR44

ON RH SIDE (IN ACCORDANCE WITH

TASK 536177Ü832Ü801Ü001) AT THE

THRESHOLD GIVEN IN THE PLANNING

INFORMATION PARAGRAPH E.(2) 02

01 THE ACCOMPLISHMENT OF THE SB 53Ü6176 REPLACES 

ALL FRAME FEET BETWEEN FR41 AND FR46

SEE FIG. AÜFFHAA SHEET 01

OR

APPLY SERVICE BULLETIN

A300Ü53Ü6176 BEFORE

NEXT FLIGHT 01

REPORT TO AIRBUS WITHIN 1 MONTH 

FROM INSPECTION DATE

REPEAT THE INSPECTION OF

THE FRAME FOOT AT FR44 ON

RH SIDE (IN ACCORDANCE WITH

TASK 536177Ü832Ü801Ü001) AT THE

INTERVAL GIVEN IN THE PLANNING

INFORMATION PARAGRAPH E.(2) 02

SEE FIG. AÜFFHAA SHEET 01

REPORT TO AIRBUS

WITHIN 1 MONTH FROM

INSPECTION DATE

NO FURTHER ACTION

NOTE:

THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE

AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR

COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN

02 REPEAT THE INSPECTION AT THE INTERVAL FOR NOT REPLACED FRAME

FOOT AND AT THE THRESHOLD FOR REPLACED FRAME FOOT

D_SB_536177_5_FHAA_02_01

Figure A-FFHAA - Sheet 02

Flow Chart for Frame 44 on RH side

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 700

5

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

SERVICE BULLETIN

**CONF 001 thru 003

CRACK FOUND IN 

AREA 1 OR AREA 2 YES NO

DO A DETAILED INSPECTION OF THE AREA 1 AND THE AREA 2 OF THE FRAME FOOT

AT FR44 ON RH SIDE (IN ACCORDANCE WITH SUBTASK 536177Ü832Ü008Ü001)

SEE FIG. AÜFFHAA SHEET 01

CRACK HIGHER THAN 

30 mm (1.181 in) NO YES

AFFECTED FRAME FOOT FOR

 LABORATORY INVESTIGATIONS AND

INFORM AIRBUS, SEND THE

PERFORM THE FOLLOWING STEPS

OR

AND DO THE CUTTINGÜOUT BEFORE NEXT FLIGHT

REPLACE THE CRACKED FRAME FOOT BY NEW ONE 

(IN ACCORDANCE WITH TASK 536177Ü833Ü801Ü001)

REPORT TO AIRBUS WITHIN 1 MONTH 

FROM INSPECTION DATE

REPEAT THE INSPECTION OF THE

REPLACED FRAME FOOT AT FR44

ON RH SIDE (IN ACCORDANCE WITH

TASK 536177Ü832Ü801Ü001) AT THE

THRESHOLD GIVEN IN THE PLANNING

INFORMATION PARAGRAPH E.(2) 02

01 THE ACCOMPLISHMENT OF THE SB 53Ü6176 REPLACES 

ALL FRAME FEET BETWEEN FR41 AND FR46

SEE FIG. AÜFFHAA SHEET 01

OR

APPLY SERVICE BULLETIN

A300Ü53Ü6176 BEFORE

NEXT FLIGHT 01

REPORT TO AIRBUS

WITHIN 1 MONTH FROM

INSPECTION DATE

NO FURTHER ACTION

NOTE:

THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE

AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR

COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN

02 REPEAT THE INSPECTION AT THE INTERVAL FOR NOT REPLACED FRAME

FOOT AND AT THE THRESHOLD FOR REPLACED FRAME FOOT

REPORT TO AIRBUS WITHIN 1 MONTH 

FROM INSPECTION DATE

REPEAT THE INSPECTION OF

THE FRAME FOOT AT FR44 ON

RH SIDE (IN ACCORDANCE WITH

TASK 536177Ü832Ü801Ü001) AT THE

INTERVAL GIVEN IN THE PLANNING

INFORMATION PARAGRAPH E.(2) 02

SEE FIG. AÜFFHAA SHEET 01

D_SB_536177_5_FHAA_03_01

Figure A-FFHAA - Sheet 03

Flow Chart for Frame 44 on RH side

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 701

5

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

SERVICE BULLETIN

**CONF 001 thru 003

CRACK FOUND IN 

AREA 2 YES NO

DO A DETAILED INSPECTION OF THE AREA 2 OF THE FRAME FOOT

AT FR44 ON RH SIDE (IN ACCORDANCE WITH SUBTASK 536177Ü832Ü008Ü001)

SEE FIG. AÜFFHAA SHEET 01

CRACK HIGHER THAN 

30 mm (1.181 in) NO YES

AFFECTED FRAME FOOT FOR

 LABORATORY INVESTIGATIONS AND

INFORM AIRBUS, SEND THE

PERFORM THE FOLLOWING STEPS

OR

AND DO THE CUTTINGÜOUT BEFORE NEXT FLIGHT

REPLACE THE CRACKED FRAME FOOT BY NEW ONE 

(IN ACCORDANCE WITH TASK 536177Ü833Ü801Ü001)

REPORT TO AIRBUS WITHIN 1 MONTH 

FROM INSPECTION DATE

REPEAT THE INSPECTION OF THE

REPLACED FRAME FOOT AT FR44

ON RH SIDE (IN ACCORDANCE WITH

TASK 536177Ü832Ü801Ü001) AT THE

THRESHOLD GIVEN IN THE PLANNING

INFORMATION PARAGRAPH E.(2) 02

01 THE ACCOMPLISHMENT OF THE SB 53Ü6176 REPLACES 

ALL FRAME FEET BETWEEN FR41 AND FR46

SEE FIG. AÜFFHAA SHEET 01

OR

APPLY SERVICE BULLETIN

A300Ü53Ü6176 BEFORE

NEXT FLIGHT 01

REPORT TO AIRBUS

WITHIN 1 MONTH FROM

INSPECTION DATE

NO FURTHER ACTION

NOTE:

THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE

AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR

COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN

02 REPEAT THE INSPECTION AT THE INTERVAL FOR NOT REPLACED FRAME

FOOT AND AT THE THRESHOLD FOR REPLACED FRAME FOOT

REPORT TO AIRBUS WITHIN 1 MONTH 

FROM INSPECTION DATE

REPEAT THE INSPECTION OF

THE FRAME FOOT AT FR44 ON

RH SIDE (IN ACCORDANCE WITH

TASK 536177Ü832Ü801Ü001) AT THE

INTERVAL GIVEN IN THE PLANNING

INFORMATION PARAGRAPH E.(2) 02

SEE FIG. AÜFFHAA SHEET 01

D_SB_536177_5_FHAA_04_01

Figure A-FFHAA - Sheet 04

Flow Chart for Frame 44 on RH side

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 702

5

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

SERVICE BULLETIN

**CONF 001 thru 003

SHEET 02 OR SHEET 03 

SEE FIG. AÜFFIAA

YES NO

FRAME FOOT

PREVENTIVELY REPAIRED

(NO CRACK) AS PER

SERVICE BULLETIN 

A300Ü53Ü6111

YES NO

FRAME FOOT REPAIRED IN

AREA 1 AS PER SERVICE BULLETIN

A300Ü53Ü6111 OR R53810322

YES NO

SEE FIG. AÜFFIAA

SHEET 02

SEE FIG. AÜFFIAA

SHEET 03

SEE FIG. AÜFFIAA

SHEET 04

VERIFY THAT THE FRAME FOOT IS COVERED BY RDAS AND

CONTACT AIRBUS WITHIN 6 MONTHS FOR FURTHER INSTRUCTIONS

DO A DETAILED INSPECTION OF THE FRAME FOOT AT FR45 ON LH SIDE (IN ACCORDANCE

INFORMATION PARAGRAPH E.(2) 

WITH TASK 536177Ü832Ü801Ü001) AT THE THRESHOLD GIVEN IN THE PLANNING

NOTE:

THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE

AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR

COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN

OR SHEET 04

NOT INSPECTED AS PER

SERVICE BULLETIN A300Ü53Ü6111 OR

 NOT REPAIRED AS PER SERVICE BULLETIN

A300Ü53Ü6111 OR NOT REPAIRED

AS PER R53810322

FRAME FOOT

D_SB_536177_5_FIAA_01_02

Figure A-FFIAA - Sheet 01

Flow Chart for Frame 45 on LH side

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 703

5

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

SERVICE BULLETIN

**CONF 001 thru 003

CRACK FOUND IN 

AREA 1 OR AREA 2 YES NO

DO A DETAILED INSPECTION OF THE AREA 1 AND THE AREA 2 OF THE FRAME FOOT

AT FR45 ON LH SIDE (IN ACCORDANCE WITH SUBTASK 536177Ü832Ü009Ü001)

SEE FIG. AÜFFIAA SHEET 01

CRACK HIGHER THAN 

30 mm (1.181 in) NO YES

AFFECTED FRAME FOOT FOR

 LABORATORY INVESTIGATIONS AND

INFORM AIRBUS, SEND THE

PERFORM THE FOLLOWING STEPS

OR

BEFORE NEXT FLIGHT

(IN ACCORDANCE WITH TASK 536177Ü833Ü801Ü001)

REPLACE THE CRACKED FRAME FOOT BY NEW ONE 

REPORT TO AIRBUS WITHIN 1 MONTH 

FROM INSPECTION DATE

REPEAT THE INSPECTION OF THE

REPLACED FRAME FOOT AT FR45

ON LH SIDE (IN ACCORDANCE WITH

TASK 536177Ü832Ü801Ü001) AT THE

THRESHOLD GIVEN IN THE PLANNING

INFORMATION PARAGRAPH E.(2) 02

01 THE ACCOMPLISHMENT OF THE SB 53Ü6176 REPLACES 

ALL FRAME FEET BETWEEN FR41 AND FR46

SEE FIG. AÜFFIAA SHEET 01

OR

APPLY SERVICE BULLETIN

A300Ü53Ü6176 BEFORE

NEXT FLIGHT 01

REPORT TO AIRBUS WITHIN 1 MONTH 

FROM INSPECTION DATE

REPEAT THE INSPECTION OF

THE FRAME FOOT AT FR45 ON

LH SIDE (IN ACCORDANCE WITH

TASK 536177Ü832Ü801Ü001) AT THE

INTERVAL GIVEN IN THE PLANNING

INFORMATION PARAGRAPH E.(2) 02

SEE FIG. AÜFFIAA SHEET 01

REPORT TO AIRBUS

WITHIN 1 MONTH FROM

INSPECTION DATE

NO FURTHER ACTION

NOTE:

THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE

AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR

COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN

02 REPEAT THE INSPECTION AT THE INTERVAL FOR NOT REPLACED FRAME

FOOT AND AT THE THRESHOLD FOR REPLACED FRAME FOOT

D_SB_536177_5_FIAA_02_01

Figure A-FFIAA - Sheet 02

Flow Chart for Frame 45 on LH side

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 704

5

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

SERVICE BULLETIN

**CONF 001 thru 003

CRACK FOUND IN 

AREA 1 OR AREA 2 YES NO

DO A DETAILED INSPECTION OF THE AREA 1 AND THE AREA 2 OF THE FRAME FOOT

AT FR45 ON LH SIDE (IN ACCORDANCE WITH SUBTASK 536177Ü832Ü009Ü001)

SEE FIG. AÜFFIAA SHEET 01

CRACK HIGHER THAN 

30 mm (1.181 in) NO YES

AFFECTED FRAME FOOT FOR

 LABORATORY INVESTIGATIONS AND

INFORM AIRBUS, SEND THE

PERFORM THE FOLLOWING STEPS

OR

AND DO THE CUTTINGÜOUT BEFORE NEXT FLIGHT

(IN ACCORDANCE WITH TASK 536177Ü833Ü801Ü001)

REPLACE THE CRACKED FRAME FOOT BY NEW ONE 

REPORT TO AIRBUS WITHIN 1 MONTH 

FROM INSPECTION DATE

REPEAT THE INSPECTION OF THE

REPLACED FRAME FOOT AT FR45

ON LH SIDE (IN ACCORDANCE WITH

TASK 536177Ü832Ü801Ü001) AT THE

THRESHOLD GIVEN IN THE PLANNING

INFORMATION PARAGRAPH E.(2) 02

01 THE ACCOMPLISHMENT OF THE SB 53Ü6176 REPLACES 

ALL FRAME FEET BETWEEN FR41 AND FR46

SEE FIG. AÜFFIAA SHEET 01

OR

APPLY SERVICE BULLETIN

A300Ü53Ü6176 BEFORE

NEXT FLIGHT 01

REPORT TO AIRBUS

WITHIN 1 MONTH FROM

INSPECTION DATE

NO FURTHER ACTION

NOTE:

THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE

AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR

COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN

02 REPEAT THE INSPECTION AT THE INTERVAL FOR NOT REPLACED FRAME

FOOT AND AT THE THRESHOLD FOR REPLACED FRAME FOOT

REPORT TO AIRBUS WITHIN 1 MONTH 

FROM INSPECTION DATE

REPEAT THE INSPECTION OF

THE FRAME FOOT AT FR45 ON

LH SIDE (IN ACCORDANCE WITH

TASK 536177Ü832Ü801Ü001) AT THE

INTERVAL GIVEN IN THE PLANNING

INFORMATION PARAGRAPH E.(2) 02

SEE FIG. AÜFFIAA SHEET 01

D_SB_536177_5_FIAA_03_01

Figure A-FFIAA - Sheet 03

Flow Chart for Frame 45 on LH side

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 705

5

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

SERVICE BULLETIN

**CONF 001 thru 003

CRACK FOUND IN 

AREA 2 YES NO

DO A DETAILED INSPECTION OF THE AREA 2 OF THE FRAME FOOT

AT FR45 ON LH SIDE (IN ACCORDANCE WITH SUBTASK 536177Ü832Ü009Ü001)

SEE FIG. AÜFFIAA SHEET 01

CRACK HIGHER THAN 

30 mm (1.181 in) NO YES

AFFECTED FRAME FOOT FOR

 LABORATORY INVESTIGATIONS AND

INFORM AIRBUS, SEND THE

PERFORM THE FOLLOWING STEPS

OR

AND DO THE CUTTINGÜOUT BEFORE NEXT FLIGHT

(IN ACCORDANCE WITH TASK 536177Ü833Ü801Ü001)

REPLACE THE CRACKED FRAME FOOT BY NEW ONE 

REPORT TO AIRBUS WITHIN 1 MONTH 

FROM INSPECTION DATE

REPEAT THE INSPECTION OF THE

REPLACED FRAME FOOT AT FR45

ON LH SIDE (IN ACCORDANCE WITH

TASK 536177Ü832Ü801Ü001) AT THE

THRESHOLD GIVEN IN THE PLANNING

INFORMATION PARAGRAPH E.(2) 02

01 THE ACCOMPLISHMENT OF THE SB 53Ü6176 REPLACES 

ALL FRAME FEET BETWEEN FR41 AND FR46

SEE FIG. AÜFFIAA SHEET 01

OR

APPLY SERVICE BULLETIN

A300Ü53Ü6176 BEFORE

NEXT FLIGHT 01

REPORT TO AIRBUS

WITHIN 1 MONTH FROM

INSPECTION DATE

NO FURTHER ACTION

NOTE:

THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE

AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR

COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN

02 REPEAT THE INSPECTION AT THE INTERVAL FOR NOT REPLACED FRAME

FOOT AND AT THE THRESHOLD FOR REPLACED FRAME FOOT

REPORT TO AIRBUS WITHIN 1 MONTH 

FROM INSPECTION DATE

REPEAT THE INSPECTION OF

THE FRAME FOOT AT FR45 ON

LH SIDE (IN ACCORDANCE WITH

TASK 536177Ü832Ü801Ü001) AT THE

INTERVAL GIVEN IN THE PLANNING

INFORMATION PARAGRAPH E.(2) 02

SEE FIG. AÜFFIAA SHEET 01

D_SB_536177_5_FIAA_04_01

Figure A-FFIAA - Sheet 04

Flow Chart for Frame 45 on LH side

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 706

5

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

SERVICE BULLETIN

**CONF 001 thru 003

SHEET 02 OR SHEET 03 

SEE FIG. AÜFFJAA

YES NO

FRAME FOOT

PREVENTIVELY REPAIRED

(NO CRACK) AS PER

SERVICE BULLETIN 

A300Ü53Ü6111

YES NO

FRAME FOOT REPAIRED IN

AREA 1 AS PER SERVICE BULLETIN 

A300Ü53Ü6111 OR R53810322

YES NO

SEE FIG. AÜFFJAA

SHEET 02

SEE FIG. AÜFFJAA

SHEET 03

SEE FIG. AÜFFJAA

SHEET 04

VERIFY THAT THE FRAME FOOT IS COVERED BY RDAS AND CONTACT

AIRBUS WITHIN 6 MONTHS FOR FURTHER INSTRUCTIONS

DO A DETAILED INSPECTION OF THE FRAME FOOT AT FR45 ON RH SIDE (IN ACCORDANCE

INFORMATION PARAGRAPH E.(2) 

WITH TASK 536177Ü832Ü801Ü001) AT THE THRESHOLD GIVEN IN THE PLANNING

NOTE:

THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE

AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR

COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN

OR SHEET 04

NOT INSPECTED AS PER

SERVICE BULLETIN A300Ü53Ü6111 OR

 NOT REPAIRED AS PER SERVICE BULLETIN

A300Ü53Ü6111 OR NOT REPAIRED

AS PER R53810322

FRAME FOOT

D_SB_536177_5_FJAA_01_02

Figure A-FFJAA - Sheet 01

Flow Chart for Frame 45 on RH side

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 707

5

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

SERVICE BULLETIN

**CONF 001 thru 003

CRACK FOUND IN 

AREA 1 OR AREA 2 YES NO

DO A DETAILED INSPECTION OF THE AREA 1 AND THE AREA 2 OF THE FRAME FOOT

AT FR45 ON RH SIDE (IN ACCORDANCE WITH SUBTASK 536177Ü832Ü010Ü001)

SEE FIG. AÜFFJAA SHEET 01

CRACK HIGHER THAN 

30 mm (1.181 in) NO YES

AFFECTED FRAME FOOT FOR

 LABORATORY INVESTIGATIONS AND

INFORM AIRBUS, SEND THE

PERFORM THE FOLLOWING STEPS

OR

BEFORE NEXT FLIGHT

(IN ACCORDANCE WITH TASK 536177Ü833Ü801Ü001)

REPLACE THE CRACKED FRAME FOOT BY NEW ONE 

REPORT TO AIRBUS WITHIN 1 MONTH 

FROM INSPECTION DATE

REPEAT THE INSPECTION OF THE

REPLACED FRAME FOOT AT FR45

ON RH SIDE (IN ACCORDANCE WITH

TASK 536177Ü832Ü801Ü001) AT THE

THRESHOLD GIVEN IN THE PLANNING

INFORMATION PARAGRAPH E.(2) 02

01 THE ACCOMPLISHMENT OF THE SB 53Ü6176 REPLACES 

ALL FRAME FEET BETWEEN FR41 AND FR46

SEE FIG. AÜFFJAA SHEET 01

OR

APPLY SERVICE BULLETIN

A300Ü53Ü6176 BEFORE

NEXT FLIGHT 01

REPORT TO AIRBUS WITHIN 1 MONTH 

FROM INSPECTION DATE

REPEAT THE INSPECTION OF

THE FRAME FOOT AT FR45 ON

RH SIDE (IN ACCORDANCE WITH

TASK 536177Ü832Ü801Ü001) AT THE

INTERVAL GIVEN IN THE PLANNING

INFORMATION PARAGRAPH E.(2) 02

SEE FIG. AÜFFJAA SHEET 01

REPORT TO AIRBUS

WITHIN 1 MONTH FROM

INSPECTION DATE

NO FURTHER ACTION

NOTE:

THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE

AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR

COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN

02 REPEAT THE INSPECTION AT THE INTERVAL FOR NOT REPLACED FRAME

FOOT AND AT THE THRESHOLD FOR REPLACED FRAME FOOT

D_SB_536177_5_FJAA_02_01

Figure A-FFJAA - Sheet 02

Flow Chart for Frame 45 on RH side

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 708

5

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

SERVICE BULLETIN

**CONF 001 thru 003

CRACK FOUND IN 

AREA 1 OR AREA 2 YES NO

DO A DETAILED INSPECTION OF THE AREA 1 AND THE AREA 2 OF THE FRAME FOOT

AT FR47 ON RH SIDE (IN ACCORDANCE WITH SUBTASK 536177Ü832Ü010Ü001)

SEE FIG. AÜFFJAA SHEET 01

CRACK HIGHER THAN 

30 mm (1.181 in) NO YES

AFFECTED FRAME FOOT FOR

 LABORATORY INVESTIGATIONS AND

INFORM AIRBUS, SEND THE

PERFORM THE FOLLOWING STEPS

OR

AND DO THE CUTTINGÜOUT BEFORE NEXT FLIGHT

(IN ACCORDANCE WITH TASK 536177Ü833Ü801Ü001)

REPLACE THE CRACKED FRAME FOOT BY NEW ONE 

REPORT TO AIRBUS WITHIN 1 MONTH 

FROM INSPECTION DATE

REPEAT THE INSPECTION OF THE

REPLACED FRAME FOOT AT FR45

ON RH SIDE (IN ACCORDANCE WITH

TASK 536177Ü832Ü801Ü001) AT THE

THRESHOLD GIVEN IN THE PLANNING

INFORMATION PARAGRAPH E.(2) 02

01 THE ACCOMPLISHMENT OF THE SB 53Ü6176 REPLACES 

ALL FRAME FEET BETWEEN FR41 AND FR46

SEE FIG. AÜFFJAA SHEET 01

OR

APPLY SERVICE BULLETIN

A300Ü53Ü6176 BEFORE

NEXT FLIGHT 01

REPORT TO AIRBUS

WITHIN 1 MONTH FROM

INSPECTION DATE

NO FURTHER ACTION

NOTE:

THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE

AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR

COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN

02 REPEAT THE INSPECTION AT THE INTERVAL FOR NOT REPLACED FRAME

FOOT AND AT THE THRESHOLD FOR REPLACED FRAME FOOT

REPORT TO AIRBUS WITHIN 1 MONTH 

FROM INSPECTION DATE

REPEAT THE INSPECTION OF

THE FRAME FOOT AT FR45 ON

RH SIDE (IN ACCORDANCE WITH

TASK 536177Ü832Ü801Ü001) AT THE

INTERVAL GIVEN IN THE PLANNING

INFORMATION PARAGRAPH E.(2) 02

SEE FIG. AÜFFJAA SHEET 01

D_SB_536177_5_FJAA_03_01

Figure A-FFJAA - Sheet 03

Flow Chart for Frame 45 on RH side

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 709

5

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

SERVICE BULLETIN

**CONF 001 thru 003

CRACK FOUND IN 

AREA 2 YES NO

DO A DETAILED INSPECTION OF THE AREA 2 OF THE FRAME FOOT

AT FR45 ON RH SIDE (IN ACCORDANCE WITH SUBTASK 536177Ü832Ü010Ü001)

SEE FIG. AÜFFJAA SHEET 01

CRACK HIGHER THAN 

30 mm (1.181 in) NO YES

AFFECTED FRAME FOOT FOR

 LABORATORY INVESTIGATIONS AND

INFORM AIRBUS, SEND THE

PERFORM THE FOLLOWING STEPS

OR

AND DO THE CUTTINGÜOUT BEFORE NEXT FLIGHT

(IN ACCORDANCE WITH TASK 536177Ü833Ü801Ü001)

REPLACE THE CRACKED FRAME FOOT BY NEW ONE

REPORT TO AIRBUS WITHIN 1 MONTH 

FROM INSPECTION DATE

REPEAT THE INSPECTION OF THE

REPLACED FRAME FOOT AT FR45

ON RH SIDE (IN ACCORDANCE WITH

TASK 536177Ü832Ü801Ü001) AT THE

THRESHOLD GIVEN IN THE PLANNING

INFORMATION PARAGRAPH E.(2) 02

01 THE ACCOMPLISHMENT OF THE SB 53Ü6176 REPLACES 

ALL FRAME FEET BETWEEN FR41 AND FR46

SEE FIG. AÜFFJAA SHEET 01

OR

APPLY SERVICE BULLETIN

A300Ü53Ü6176 BEFORE

NEXT FLIGHT 01

REPORT TO AIRBUS

WITHIN 1 MONTH FROM

INSPECTION DATE

NO FURTHER ACTION

NOTE:

THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE

AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR

COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN

02 REPEAT THE INSPECTION AT THE INTERVAL FOR NOT REPLACED FRAME

FOOT AND AT THE THRESHOLD FOR REPLACED FRAME FOOT

REPORT TO AIRBUS WITHIN 1 MONTH 

FROM INSPECTION DATE

REPEAT THE INSPECTION OF

THE FRAME FOOT AT FR45 ON

RH SIDE (IN ACCORDANCE WITH

TASK 536177Ü832Ü801Ü001) AT THE

INTERVAL GIVEN IN THE PLANNING

INFORMATION PARAGRAPH E.(2) 02

SEE FIG. AÜFFJAA SHEET 01

D_SB_536177_5_FJAA_04_01

Figure A-FFJAA - Sheet 04

Flow Chart for Frame 45 on RH side

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 710

5

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

SERVICE BULLETIN

**CONF 001 thru 003

SHEET 02 OR SHEET 03 

SEE FIG. AÜFFKAA

OR SHEET 04

YES NO

FRAME FOOT PREVENTIVELY 

REPAIRED (NO CRACK) 

AS PER

YES NO

SERVICE BULLETIN 

A300Ü53Ü6111

FRAME FOOT REPAIRED IN AREA 1 

AS PER SERVICE BULLETIN 

A300Ü53Ü6111 OR R53810323

YES NO

SEE FIG. AÜFFKAA

SHEET 02

SEE FIG. AÜFFKAA

SHEET 03

SEE FIG. AÜFFKAA

SHEET 04

VERIFY THAT THE FRAME FOOT IS COVERED BY RDAS AND CONTACT 

AIRBUS WITHIN 6 MONTHS FOR FURTHER INSTRUCTIONS

DO A DETAILED INSPECTION OF THE FRAME FOOT AT FR46 ON LH SIDE (IN ACCORDANCE

INFORMATION PARAGRAPH E.(2) 

WITH TASK 536177Ü832Ü801Ü001) AT THE THRESHOLD GIVEN IN THE PLANNING

NOTE:

THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE

AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR

COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN

NOT INSPECTED AS PER

SERVICE BULLETIN A300Ü53Ü6111 OR

 NOT REPAIRED AS PER SERVICE BULLETIN

A300Ü53Ü6111 OR NOT REPAIRED

AS PER R53810323

FRAME FOOT

D_SB_536177_5_FKAA_01_02

Figure A-FFKAA - Sheet 01

Flow Chart for Frame 46 on LH side

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 711

5

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

SERVICE BULLETIN

**CONF 001 thru 003

CRACK FOUND IN 

AREA 1 OR AREA 2 YES NO

DO A DETAILED INSPECTION OF THE AREA 1 AND THE AREA 2 OF THE FRAME FOOT

AT FR46 ON LH SIDE (IN ACCORDANCE WITH SUBTASK 536177Ü832Ü011Ü001)

SEE FIG. AÜFFKAA SHEET 01

CRACK HIGHER THAN 

30 mm (1.181 in) NO YES

AFFECTED FRAME FOOT FOR

 LABORATORY INVESTIGATIONS AND

INFORM AIRBUS, SEND THE

PERFORM THE FOLLOWING STEPS

OR

BEFORE NEXT FLIGHT

REPLACE THE CRACKED FRAME FOOT BY NEW ONE 

(IN ACCORDANCE WITH TASK 536177Ü833Ü801Ü001)

REPORT TO AIRBUS WITHIN 1 MONTH 

FROM INSPECTION DATE

REPEAT THE INSPECTION OF THE

REPLACED FRAME FOOT AT FR46

ON LH SIDE (IN ACCORDANCE WITH

TASK 536177Ü832Ü801Ü001) AT THE

THRESHOLD GIVEN IN THE PLANNING

INFORMATION PARAGRAPH E.(2) 02

01 THE ACCOMPLISHMENT OF THE SB 53Ü6176 REPLACES 

ALL FRAME FEET BETWEEN FR41 AND FR46

SEE FIG. AÜFFKAA SHEET 01

OR

APPLY SERVICE BULLETIN

A300Ü53Ü6176 BEFORE

NEXT FLIGHT 01

REPORT TO AIRBUS WITHIN 1 MONTH 

FROM INSPECTION DATE

REPEAT THE INSPECTION OF

THE FRAME FOOT AT FR46 ON

LH SIDE (IN ACCORDANCE WITH

TASK 536177Ü832Ü801Ü001) AT THE

INTERVAL GIVEN IN THE PLANNING

INFORMATION PARAGRAPH E.(2) 02

SEE FIG. AÜFFKAA SHEET 01

REPORT TO AIRBUS

WITHIN 1 MONTH FROM

INSPECTION DATE

NO FURTHER ACTION

NOTE:

THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE

AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR

COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN

02 REPEAT THE INSPECTION AT THE INTERVAL FOR NOT REPLACED FRAME

FOOT AND AT THE THRESHOLD FOR REPLACED FRAME FOOT

D_SB_536177_5_FKAA_02_01

Figure A-FFKAA - Sheet 02

Flow Chart for Frame 46 on LH side

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 712

5

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

SERVICE BULLETIN

**CONF 001 thru 003

CRACK FOUND IN 

AREA 1 OR AREA 2 YES NO

DO A DETAILED INSPECTION OF THE AREA 1 AND THE AREA 2 OF THE FRAME FOOT

AT FR46 ON LH SIDE (IN ACCORDANCE WITH SUBTASK 536177Ü832Ü011Ü001)

SEE FIG. AÜFFKAA SHEET 01

CRACK HIGHER THAN 

30 mm (1.181 in) NO YES

AFFECTED FRAME FOOT FOR

 LABORATORY INVESTIGATIONS AND

INFORM AIRBUS, SEND THE

PERFORM THE FOLLOWING STEPS

OR

AND DO THE CUTTINGÜOUT BEFORE NEXT FLIGHT

REPLACE THE CRACKED FRAME FOOT BY NEW ONE 

(IN ACCORDANCE WITH TASK 536177Ü833Ü801Ü001)

REPORT TO AIRBUS WITHIN 1 MONTH 

FROM INSPECTION DATE

REPEAT THE INSPECTION OF THE

REPLACED FRAME FOOT AT FR46

ON LH SIDE (IN ACCORDANCE WITH

TASK 536177Ü832Ü801Ü001) AT THE

THRESHOLD GIVEN IN THE PLANNING

INFORMATION PARAGRAPH E.(2) 02

01 THE ACCOMPLISHMENT OF THE SB 53Ü6176 REPLACES 

ALL FRAME FEET BETWEEN FR41 AND FR46

SEE FIG. AÜFFKAA SHEET 01

OR

APPLY SERVICE BULLETIN

A300Ü53Ü6176 BEFORE

NEXT FLIGHT 01

REPORT TO AIRBUS

WITHIN 1 MONTH FROM

INSPECTION DATE

NO FURTHER ACTION

NOTE:

THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE

AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR

COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN

02 REPEAT THE INSPECTION AT THE INTERVAL FOR NOT REPLACED FRAME

FOOT AND AT THE THRESHOLD FOR REPLACED FRAME FOOT

REPORT TO AIRBUS WITHIN 1 MONTH 

FROM INSPECTION DATE

REPEAT THE INSPECTION OF

THE FRAME FOOT AT FR46 ON

LH SIDE (IN ACCORDANCE WITH

TASK 536177Ü832Ü801Ü001) AT THE

INTERVAL GIVEN IN THE PLANNING

INFORMATION PARAGRAPH E.(2) 02

SEE FIG. AÜFFKAA SHEET 01

D_SB_536177_5_FKAA_03_01

Figure A-FFKAA - Sheet 03

Flow Chart for Frame 46 on LH side

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 713

5

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

SERVICE BULLETIN

**CONF 001 thru 003

CRACK FOUND IN 

AREA 2 YES NO

DO A DETAILED INSPECTION OF THE AREA 2 OF THE FRAME FOOT

AT FR46 ON LH SIDE (IN ACCORDANCE WITH SUBTASK 536177Ü832Ü011Ü001)

SEE FIG. AÜFFKAA SHEET 01

CRACK HIGHER THAN 

30 mm (1.181 in) NO YES

AFFECTED FRAME FOOT FOR

 LABORATORY INVESTIGATIONS AND

INFORM AIRBUS, SEND THE

PERFORM THE FOLLOWING STEPS

OR

AND DO THE CUTTINGÜOUT BEFORE NEXT FLIGHT

REPLACE THE CRACKED FRAME FOOT BY NEW ONE 

(IN ACCORDANCE WITH TASK 536177Ü833Ü801Ü001)

REPORT TO AIRBUS WITHIN 1 MONTH 

FROM INSPECTION DATE

REPEAT THE INSPECTION OF THE

REPLACED FRAME FOOT AT FR46

ON LH SIDE (IN ACCORDANCE WITH

TASK 536177Ü832Ü801Ü001) AT THE

THRESHOLD GIVEN IN THE PLANNING

INFORMATION PARAGRAPH E.(2) 02

01 THE ACCOMPLISHMENT OF THE SB 53Ü6176 REPLACES 

ALL FRAME FEET BETWEEN FR41 AND FR46

SEE FIG. AÜFFKAA SHEET 01

OR

APPLY SERVICE BULLETIN

A300Ü53Ü6176 BEFORE

NEXT FLIGHT 01

REPORT TO AIRBUS

WITHIN 1 MONTH FROM

INSPECTION DATE

NO FURTHER ACTION

NOTE:

THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE

AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR

COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN

02 REPEAT THE INSPECTION AT THE INTERVAL FOR NOT REPLACED FRAME

FOOT AND AT THE THRESHOLD FOR REPLACED FRAME FOOT

REPORT TO AIRBUS WITHIN 1 MONTH 

FROM INSPECTION DATE

REPEAT THE INSPECTION OF

THE FRAME FOOT AT FR46 ON

LH SIDE (IN ACCORDANCE WITH

TASK 536177Ü832Ü801Ü001) AT THE

INTERVAL GIVEN IN THE PLANNING

INFORMATION PARAGRAPH E.(2) 02

SEE FIG. AÜFFKAA SHEET 01

D_SB_536177_5_FKAA_04_01

Figure A-FFKAA - Sheet 04

Flow Chart for Frame 46 on LH side

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 714

5

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

SERVICE BULLETIN

**CONF 001 thru 003

SHEET 02 OR SHEET 03 

SEE FIG. AÜFFLAA

OR SHEET 04

YES NO

FRAME FOOT PREVENTIVELY 

REPAIRED (NO CRACK) 

AS PER

YES NO

SERVICE BULLETIN 

A300Ü53Ü6111

FRAME FOOT REPAIRED IN AREA 1 

AS PER SERVICE BULLETIN 

A300Ü53Ü6111 OR R53810323

YES NO

SEE FIG. AÜFFLAA

SHEET 02

SEE FIG. AÜFFLAA

SHEET 03

SEE FIG. AÜFFLAA

SHEET 04

VERIFY THAT THE FRAME FOOT IS COVERED BY RDAS AND CONTACT 

AIRBUS WITHIN 6 MONTHS FOR FURTHER INSTRUCTIONS

DO A DETAILED INSPECTION OF THE FRAME FOOT AT FR46 ON RH SIDE (IN ACCORDANCE

INFORMATION PARAGRAPH E.(2) 

WITH TASK 536177Ü832Ü801Ü001) AT THE THRESHOLD GIVEN IN THE PLANNING

NOTE:

THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE

AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR

COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN

NOT INSPECTED AS PER

SERVICE BULLETIN A300Ü53Ü6111 OR

 NOT REPAIRED AS PER SERVICE BULLETIN

A300Ü53Ü6111 OR NOT REPAIRED

AS PER R53810323

FRAME FOOT

D_SB_536177_5_FLAA_01_02

Figure A-FFLAA - Sheet 01

Flow Chart for Frame 46 on RH side

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 715

5

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

SERVICE BULLETIN

**CONF 001 thru 003

CRACK FOUND IN 

AREA 1 OR AREA 2 YES NO

DO A DETAILED INSPECTION OF THE AREA 1 AND THE AREA 2 OF THE FRAME FOOT

AT FR46 ON RH SIDE (IN ACCORDANCE WITH SUBTASK 536177Ü832Ü012Ü001)

SEE FIG. AÜFFLAA SHEET 01

CRACK HIGHER THAN 

30 mm (1.181 in) NO YES

AFFECTED FRAME FOOT FOR

 LABORATORY INVESTIGATIONS AND

INFORM AIRBUS, SEND THE

PERFORM THE FOLLOWING STEPS

OR

BEFORE NEXT FLIGHT

REPLACE THE CRACKED FRAME FOOT BY NEW ONE 

(IN ACCORDANCE WITH TASK 536177Ü833Ü801Ü001)

REPORT TO AIRBUS WITHIN 1 MONTH 

FROM INSPECTION DATE

REPEAT THE INSPECTION OF THE

REPLACED FRAME FOOT AT FR46

ON RH SIDE (IN ACCORDANCE WITH

TASK 536177Ü832Ü801Ü001) AT THE

THRESHOLD GIVEN IN THE PLANNING

INFORMATION PARAGRAPH E.(2) 02

01 THE ACCOMPLISHMENT OF THE SB 53Ü6176 REPLACES 

ALL FRAME FEET BETWEEN FR41 AND FR46

SEE FIG. AÜFFLAA SHEET 01

OR

APPLY SERVICE BULLETIN

A300Ü53Ü6176 BEFORE

NEXT FLIGHT 01

REPORT TO AIRBUS WITHIN 1 MONTH 

FROM INSPECTION DATE

REPEAT THE INSPECTION OF

THE FRAME FOOT AT FR46 ON

RH SIDE (IN ACCORDANCE WITH

TASK 536177Ü832Ü801Ü001) AT THE

INTERVAL GIVEN IN THE PLANNING

INFORMATION PARAGRAPH E.(2) 02

SEE FIG. AÜFFLAA SHEET 01

REPORT TO AIRBUS

WITHIN 1 MONTH FROM

INSPECTION DATE

NO FURTHER ACTION

NOTE:

THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE

AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR

COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN

02 REPEAT THE INSPECTION AT THE INTERVAL FOR NOT REPLACED FRAME

FOOT AND AT THE THRESHOLD FOR REPLACED FRAME FOOT

D_SB_536177_5_FLAA_02_01

Figure A-FFLAA - Sheet 02

Flow Chart for Frame 46 on RH side

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 716

5

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

SERVICE BULLETIN

**CONF 001 thru 003

CRACK FOUND IN 

AREA 1 OR AREA 2 YES NO

DO A DETAILED INSPECTION OF THE AREA 1 AND THE AREA 2 OF THE FRAME FOOT

AT FR46 ON RH SIDE (IN ACCORDANCE WITH SUBTASK 536177Ü832Ü012Ü001)

SEE FIG. AÜFFLAA SHEET 01

CRACK HIGHER THAN 

30 mm (1.181 in) NO YES

AFFECTED FRAME FOOT FOR

 LABORATORY INVESTIGATIONS AND

INFORM AIRBUS, SEND THE

PERFORM THE FOLLOWING STEPS

OR

AND DO THE CUTTINGÜOUT BEFORE NEXT FLIGHT

REPLACE THE CRACKED FRAME FOOT BY NEW ONE 

(IN ACCORDANCE WITH TASK 536177Ü833Ü801Ü001)

REPORT TO AIRBUS WITHIN 1 MONTH 

FROM INSPECTION DATE

REPEAT THE INSPECTION OF THE

REPLACED FRAME FOOT AT FR46

ON RH SIDE (IN ACCORDANCE WITH

TASK 536177Ü832Ü801Ü001) AT THE

THRESHOLD GIVEN IN THE PLANNING

INFORMATION PARAGRAPH E.(2) 02

01 THE ACCOMPLISHMENT OF THE SB 53Ü6176 REPLACES 

ALL FRAME FEET BETWEEN FR41 AND FR46

SEE FIG. AÜFFLAA SHEET 01

OR

APPLY SERVICE BULLETIN

A300Ü53Ü6176 BEFORE

NEXT FLIGHT 01

REPORT TO AIRBUS

WITHIN 1 MONTH FROM

INSPECTION DATE

NO FURTHER ACTION

NOTE:

THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE

AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR

COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN

02 REPEAT THE INSPECTION AT THE INTERVAL FOR NOT REPLACED FRAME

FOOT AND AT THE THRESHOLD FOR REPLACED FRAME FOOT

REPORT TO AIRBUS WITHIN 1 MONTH 

FROM INSPECTION DATE

REPEAT THE INSPECTION OF

THE FRAME FOOT AT FR46 ON

RH SIDE (IN ACCORDANCE WITH

TASK 536177Ü832Ü801Ü001) AT THE

INTERVAL GIVEN IN THE PLANNING

INFORMATION PARAGRAPH E.(2) 02

SEE FIG. AÜFFLAA SHEET 01

D_SB_536177_5_FLAA_03_01

Figure A-FFLAA - Sheet 03

Flow Chart for Frame 46 on RH side

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 717

5

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

SERVICE BULLETIN

**CONF 001 thru 003

CRACK FOUND IN 

AREA 2 YES NO

DO A DETAILED INSPECTION OF THE AREA 2 OF THE FRAME FOOT

AT FR46 ON RH SIDE (IN ACCORDANCE WITH SUBTASK 536177Ü832Ü012Ü001)

SEE FIG. AÜFFLAA SHEET 01

CRACK HIGHER THAN 

30 mm (1.181 in) NO YES

AFFECTED FRAME FOOT FOR

 LABORATORY INVESTIGATIONS AND

INFORM AIRBUS, SEND THE

PERFORM THE FOLLOWING STEPS

OR

AND DO THE CUTTINGÜOUT BEFORE NEXT FLIGHT

REPLACE THE CRACKED FRAME FOOT BY NEW ONE 

(IN ACCORDANCE WITH TASK 536177Ü833Ü801Ü001)

REPORT TO AIRBUS WITHIN 1 MONTH 

FROM INSPECTION DATE

REPEAT THE INSPECTION OF THE

REPLACED FRAME FOOT AT FR46

ON RH SIDE (IN ACCORDANCE WITH

TASK 536177Ü832Ü801Ü001) AT THE

THRESHOLD GIVEN IN THE PLANNING

INFORMATION PARAGRAPH E.(2) 02

01 THE ACCOMPLISHMENT OF THE SB 53Ü6176 REPLACES 

ALL FRAME FEET BETWEEN FR41 AND FR46

SEE FIG. AÜFFLAA SHEET 01

OR

APPLY SERVICE BULLETIN

A300Ü53Ü6176 BEFORE

NEXT FLIGHT 01

REPORT TO AIRBUS

WITHIN 1 MONTH FROM

INSPECTION DATE

NO FURTHER ACTION

NOTE:

THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE

AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR

COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN

02 REPEAT THE INSPECTION AT THE INTERVAL FOR NOT REPLACED FRAME

FOOT AND AT THE THRESHOLD FOR REPLACED FRAME FOOT

REPORT TO AIRBUS WITHIN 1 MONTH 

FROM INSPECTION DATE

REPEAT THE INSPECTION OF

THE FRAME FOOT AT FR46 ON

RH SIDE (IN ACCORDANCE WITH

TASK 536177Ü832Ü801Ü001) AT THE

INTERVAL GIVEN IN THE PLANNING

INFORMATION PARAGRAPH E.(2) 02

SEE FIG. AÜFFLAA SHEET 01

D_SB_536177_5_FLAA_04_01

Figure A-FFLAA - Sheet 04

Flow Chart for Frame 46 on RH side

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 718

5

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

SERVICE BULLETIN

**CONF ALL

C

INSPECTION REPORT

SERVICE BULLETIN No :

A/C MSN :

FLIGHT CYCLES :

FLIGHT HOURS :

A300Ü53Ü6177

DATE OF INSPECTION :

INSPECTION METHOD : DETAILED

INSPECTION

CL

FR41

FR42

FR43

FR44

FR45

FR46

A

FR40

FR47

C

B

AREA 1

AREA 2

LH SHOWN

RH SYMMETRICAL

C

RETURN TO :

AIRBUS

CUSTOMER SERVICES ENGINEERING Ü SEES1

DOORS Ü FUSELAGE Ü CWB Ü WINDOWS

1 ROND POINT MAURICE BELLONTE

31707 BLAGNAC CEDEX

FRANCE

EÜMAIL: structure.sbinspectionresult@airbus.com

FAX: +33 (0)5 61 93 36 14

NOTE:

AREA TO BE INSPECTED

A

B

B

D_SB_536177_5_RAAA_01_01

Figure A-FRAAA - Sheet 01

Inspection report

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 719

5

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

SERVICE BULLETIN

**CONF ALL

INSPECTION REPORT

SERVICE BULLETIN No :

A/C MSN :

FLIGHT CYCLES :

FLIGHT HOURS :

A300Ü53Ü6177

DATE OF INSPECTION :

INSPECTION METHOD : DETAILED

INSPECTION

FRAME

CRACK

NOT

CHECKED YES NO

LENGTH

AREA 1

YES NO

CRACK

LENGTH

AREA 2 REPLACED

FRAME FOOT

YES NO

41 LH

42 LH

43 LH

44 LH

45 LH

46 LH

41 RH

42 RH

43 RH

44 RH

45 RH

46 RH

SB 53Ü6176 APPLIED: YES

NO

PLEASE PRECISE OTHER FINDINGS:

RETURN TO :

AIRBUS

CUSTOMER SERVICES ENGINEERING Ü SEES1

DOORS Ü FUSELAGE Ü CWB Ü WINDOWS

1 ROND POINT MAURICE BELLONTE

31707 BLAGNAC CEDEX

FRANCE

EÜMAIL: structure.sbinspectionresult@airbus.com

FAX: +33 (0)5 61 93 36 14

D_SB_536177_5_RAAA_02_01

Figure A-FRAAA - Sheet 02

Inspection report

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 720

5

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

SERVICE BULLETIN

Appendix 01 - Elapsed Time Assumptions

**CONF 001 thru 003

For an explanation of the manhours and elapsed time, refer to the following Gantt Chart.

**CONF 004

None

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 1

5

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

SERVICE BULLETIN

Appendix 01 - Elapsed Time Assumptions

**CONF 001 thru 003

ELAPSED TIME ASSUMPTION SERVICE BULLETIN No A300Ü53Ü6177

GET ACCESS

MH ET/S

TOTAL MANHOURS

SB ELAPSED TIME

8.00

2.50

STEPS

1.00 1.00

0 2.5

CLOSEÜUP

MH

ET/S:

PER

MANHOURS

ELAPSED TIME PER STEP

NUMBER OF PERSONS

01

02

THIS CHART IS ONLY A PROPOSAL.

OPERATORS MAY DETERMINE THAT ANOTHER WAY

TO DO THE WORK IS MORE SUITABLE FOR THEM.

01

02

NOTE:

PER

1

:

:

SB ELAPSED TIME

(HOURS)

0.5 1 1.5 2

IF A VSB IS INVOLVED, THE ASSOCIATED MANHOURS

ARE NOT REFLECTED IN THIS GANTT CHART.

DO A DETAILED INSPECTION OF THE

FRAME FOOT AT FR41 ON LH SIDE

DO A DETAILED INSPECTION OF THE

FRAME FOOT AT FR41 ON RH SIDE

DO A DETAILED INSPECTION OF THE

FRAME FOOT AT FR42 ON LH SIDE

DO A DETAILED INSPECTION OF THE

FRAME FOOT AT FR42 ON RH SIDE

DO A DETAILED INSPECTION OF THE

FRAME FOOT AT FR43 ON LH SIDE

DO A DETAILED INSPECTION OF THE

FRAME FOOT AT FR43 ON RH SIDE

DO A DETAILED INSPECTION OF THE

FRAME FOOT AT FR44 ON LH SIDE

DO A DETAILED INSPECTION OF THE

FRAME FOOT AT FR44 ON RH SIDE

DO A DETAILED INSPECTION OF THE

FRAME FOOT AT FR45 ON LH SIDE

DO A DETAILED INSPECTION OF THE

FRAME FOOT AT FR45 ON RH SIDE

DO A DETAILED INSPECTION OF THE

FRAME FOOT AT FR46 ON LH SIDE

DO A DETAILED INSPECTION OF THE

FRAME FOOT AT FR46 ON RH SIDE

0.50 0.50 1

0.50 0.50 1

0.50 0.50 1

0.50 0.50 1

0.50 0.50 1

0.50 0.50 1

0.50 0.50 1

0.50 0.50 1

0.50 0.50 1

0.50 0.50 1

0.50 0.50 1

0.50 0.50 1

1.00 1.00 1

D_SB_536177_5_AAAA_01_00

Figure A-FAAAA - Sheet 01

Gantt Chart

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 2

5

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

SERVICE BULLETIN

REPORTING SHEET

TITLE: FUSELAGE - CENTER FUSELAGE - INSPECT LOWER FRAME BASE

FITTING BETWEEN FRAMES 41 AND 46

MODIFICATION No.: None

Please complete the appropriate item (A or B):

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

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

embodiment:

B - SB HAS BEEN embodied on aircraft:

Operator comments:

From Airline:

Name/Title:

Signature: Date:

If operational documentation is affected (see Paragraph 1.K of this SB): If information is needed prior to

next normal revision or prior to SB embodiment, please indicate required service(s):

Either: Modification Operational Impact (MOI), if available YES/NO

Or : Intermediate revision YES/NO

Important Information: This SB will only be incorporated in your maintenance and operational

documentation if this sheet is returned to Airbus and signed by a duly authorised representative. With

the next feasible revision, this will result in

- Updating of maintenance documentation to show pre and post SB data.

- Updating of maintenance and operational documentation to show post SB data after embodiment.

If this SB requires previous or simultaneous accomplishment of other SBs, Airbus shall automatically

include them in the manual revisions. Refer to SIL 00-037 for detailed information.

Please return this completed sheet to:

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX FRANCE

Attn: SDC32 Technical Data and Documentation Services

FAX: (+33) 5 61 93 28 06

e-mail: sb.reporting@airbus.com

or via your Resident Customer Support Office.

Alternatively, SB lists via letters or fax are also accepted.

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 1

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@A300-600

SERVICE BULLETIN

QUALITY PERCEPTION FORM

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

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

improve the quality of our Service Bulletins.

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

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

- Quality rating of this SB 4321

- Quality rating of the Accomplishment Instructions 4321

- Quality rating of the Illustrations 4321

- Is this SB easy to understand ? Y/N

If you have had difficulties in the accomplishment of this SB please quote below the area(s) and give a

short description of the issue.

Planning Material Instructions

X Effectivity X Kit content X Preparation

X Reason X List of Materials Operator Supplied X Mod/Inspection

X Manpower X Industry support X Test

X References X Re-identification X Close-Up

X Publication X Tooling X Illustrations

Comments:

Operator: Date:

Name/Title:

Please return this form to:

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX FRANCE

Attn : SEM4 Service Bulletins Management

FAX : (33) 5 61 93 42 51

Or via your Resident Customer Support Office.

DATE: May 20/15 SERVICE BULLETIN No.: A300-53-6177

REVISION No.: 00 - May 20/15 Page: 1

5

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