5 DATE : Sep 09/94 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 22/06 Page : 1 of 

Printed in FRANCE © AIRBUS, 2006 All rights reserved

MANDATORY MANDATORY MAND

ATA SYSTEM : 57

TITLE : WINGS-SECTION 21-INSPECTION OF HOLES "H"AND "I" OF THE CO

FITTING.

MODIFICATION No. : None

This page transmits Revision No. 07 of Service Bulletin No. A300-

ADDITIONAL WORK

No additional work is required by this revision for aircraft m

previous issue.

REASON

Accomplishment of Service Bulletin No. A300-57-6069 cancels t

of inspection of holes H and I of the corner angle fitting de

Service Bulletin and cancels the requirement of inspection of 

and bottom panel at junction with fuselage defined in Service 

A300-57-6086.

CHANGES

SUMMARY :

— REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

. Sentence Concerning the Airworthiness Directive (Consign

Navigabilite) deleted. Sentence added. In the EVALUATION T

Airworthiness Directive number deleted.

— EFFECTIVITY

. Operators updated.

PLANNING INFORMATION :

— EFFECTIVITY

. 1.A. Effectivity updated.

— REASON
DATE : Sep 09/94 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 22/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

. 1.F. Sentence updated.

— REFERENCES

. 1.J. Reference to Service Bulletins No. A300-57-6069 and A

added. Reference to Airworthiness Directive No. 2000-533-

MATERIAL INFORMATION :

— MATERIAL - PRICE AND AVAILABILITY

. 2.A. Address updated.

ACCOMPLISHMENT INSTRUCTIONS :

— GENERAL

. 3.A. Warning updated.

FILING INSTRUCTIONS

This Service Bulletin has been generated electronically and is 

complete document. Replace the complete document.

Put this Revision Transmittal Sheet in front of the Service B

HISTORY OF PREVIOUS REVISIONS

This is only applicable for Revision No. 05 and subsequent. I

is required for Revisions issued previous to this, please che

of Revision Transmittal Sheets or contact AIRBUS.

Revision No. 05 issued to create a Kit A08 valid for A/C post 

Bulletin No. A300-57-6050. Fasteners length updated to match 

Service Bulletin No. A300-57-6050. Fastener hole H added in K

Revision No. 06 issued to update the thresholds and intervals, 

operators that the Airworthiness Directive/Consigne de Naviga

1999-147-279 becomes No. 2000-533-328(B), the Para. EFFECTIVIT

and new inspection of holes U, V, W, X, Y for configurations 

03 added.

This Service Bulletin has been entirely re-written, in order 

easier understanding of the inspection to be carried out.

2
DATE : Sep 09/94 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 22/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

REVISION No. : 05 — Sep 14/01

REVISION No. : 06 — Jul 15/04

REVISION No. : 07 — Dec 22/06

3
5 DATE : Sep 09/94 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 22/06 Page : 1 of 

Printed in FRANCE © AIRBUS, 2006 All rights reserved

This summary is for information only

and is not approved for modification of the aircraf

MANDATORY MANDATORY MAND

ATA SYSTEM : 57

TITLE : WINGS-SECTION 21-INSPECTION OF HOLES "H"AND "I" OF THE CO

FITTING.

MODIFICATION No. : None

REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

Cracks have been found on A300 B2/B4 fleet at about 20,000 flight

forward fitting at the level of last fastener of external angle f

Cracks if undetected can increase in magnitude in rear spar and p

reducing the residual strength capacity of the structure and requ

extensive structural repair.

The in-service experience from the application of inspection on t

A300-600 fleets shows that:

— Cracks have been found before reaching the threshold.

— Cracks have been found in other holes (basically holes H and I w

during accomplishment of modification Service Bulletins No. A30

A300-57-6050.

Revision No.03 of this Service Bulletin takes this new data into 

From Revision No.03 of this SB, further in service experience hav

cracks have been found in other holes than holes H, I, K, L, M an

why Revision No.06 request to inspect new holes U, V, W, X and Y 

take these new findings into account.

The aim of this Service Bulletin is to call for eddy current inspe

H, I, K, L, M, N and U, V, W, X, Y in LH and RH internal angles o

box.

This inspection will make it possible to detect crack propagation 

stage, thus avoiding an extensive repair.

Accomplishment of Service Bulletin No. A300-57-6069 cancels the r

inspection of holes H and I of the corner angle fitting defined i
DATE : Sep 09/94 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 22/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

EFFECTIVITY

This Service Bulletin is applicable to these operators :

51Y 90X AAL ABD AWW CAL CES CSN DLH FDX HLF I2L IRA JLJ KAC KAL LA

OAL OHY QTR SUD SVA TAR THA

CONCURRENT REQUIREMENTS

None

REFERENCES/REPERCUSSIONS

TFU : 57.10.00.003

OEB : None

AOT : None

SIL : 53-057

LIFE LIMIT : None

LINE MAINTENANCE AFFECTED : No

OTHERS : None

NATURE OF THE WORK

AIRCRAFT : YES

EQUIPMENT : NO

HARD : NO

SOFT : NO

OBRM : NO

MANPOWER

Inspection LH and RH sides, Config. 01 or 02 or 03 or 04

AD Yes A/C OPERATION AFFECT

RELIABILITY AFFECTED No PAX COMFORT AFFECTED 

COST SAVING No ETOPS AFFECTED 

STRUCTURAL LIFE EXTN No VENDOR SB INVOLVED 

KIT PRICE (USD) See SB

TOTAL MANHOURS 

ELAPSED TIME (HOURS) 

2
DATE : Sep 09/94 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 22/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

MATERIAL INFORMATION

AIRCRAFT DATA

Kit 576049A01R05 : 4 bolts

Kit 576049A02R06 : 4 bolts

Kit 576049A03R09 : 6 bolts

Kit 576049A04R06 : 12 bolts

Kit 576049A05R06 : 12 bolts

Kit 576049A06R04 : 16 bolts

Kit 576049A07R03 : 56 bolts

Kit 576049A08R01 : 12 bolts

Kit 576049A09R00 : 20 bolts

Kit 576049A10R00 : 10 bolts

APPENDICES

Yes: see Appendix 01

TOTAL MANHOURS 

ELAPSED TIME (HOURS) 

3
DATE : Sep 09/94 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 22/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

4
5 DATE : Sep 09/94 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 22/06 Page : 1 of 

Printed in FRANCE © AIRBUS, 2006 All rights reserved

MANDATORY MANDATORY MAND

ATA SYSTEM : 57

TITLE : WINGS-SECTION 21-INSPECTION OF HOLES "H"AND "I" OF THE CO

FITTING.

MODIFICATION No. : None

This document contains Airbus PROPRIETARY INFORMATION and shall a

remain the property of Airbus; no intellectual property right or 

granted by Airbus in connection with any information contained in 

delivered on the express condition that said document and the inf

contained in it shall be treated as confidential, shall not be us

purpose other than that for which it is hereby delivered. It shal

disclosed in whole or in part to third parties and shall not be d

any manner (except for the purposes of performing the tasks descr

and provided that any recipient of such document shall comply wit

conditions herein), without Airbus's prior written consent.

1. PLANNING INFORMATION

A. EFFECTIVITY

(1) Models

B4-601 B4-603 B4-605R B4-620 B4-622 B4-622R C4-605R/

F4-605R

(2) Aircraft

(a) Effectivity by MSN

This Service Bulletin is applicable to aircraft 

0252 0284 0294 0301 0307 0312 0317 0321 0336 034

0351 0354 0358 0361 0365 0368 0371 0377 0380 03

0395 0398 0401 0405 0408 0411 0414 0417 0423 04

0469-0471 0474 0477 0479 0505-0518 0521 0525 05

0533 0536 0540 0543 0546 0553-0561 0563 0566 05

0577 0579 0581 0582 0584 0601-0619 0621 0623 06

0637 0639 0641 0643 0645 0657 0659 0662 0664 06

0673 0675 0677 0679 0681 0683 0685 0688 0690 069

0699 0701 0703 0705 0707 0709 0711 0713 0715 07

0721-0750 0752-0764 0766-0775 0777-0794 0797 079
DATE : Sep 09/94 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 22/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

and is correct at the time of issue in accordan

information available to Airbus. Any future cha

from transfer of an aircraft from one operator t

not be reflected in this list unless the Service 

revised for another reason.

OPERATOR MSN

51Y 0533

90X 0666

AAL 0423 0459 0460 0461 0462 0463 0465 0

0471 0474 0506 0507 0508 0509 0510 0

0514 0515 0516 0517 0606 0610 0612 0

0639 0643 0645 0675

ABD 0529 0557 0755 0758 0775

AWW 0633

CAL 0536 0555 0625 0743 0767 0788

CES 0521 0525 0532 0707 0709 0713 0715 0

0746 0754 0763

CSN 0733 0734 0739 0750 0756 0762

DLH 0380 0391 0401 0405 0408 0411 0414 0

0618 0623 0701

FDX 0358 0361 0365 0388 0417 0477 0479 0

0572 0579 0581 0657 0659 0726 0728 0

0742 0745 0748 0752 0757 0759 0760 0

0769 0771 0772 0774 0777 0778 0779 0

0790 0791 0792 0793 0794 0799 0800 0

0804

HLF 0773

I2L 0677

IRA 0632 0696 0723 0727

JLJ 0602 0617 0621 0637 0641 0670 0679 0

0724 0729 0730 0737 0740 0753 0770 0

KAC 0344 0673 0694 0699 0719 0721

KAL 0582 0609 0627 0631 0662 0685 0692 0

LAA 0601 0616

MON 0540 0556 0604 0605

MSR 0561 0575 0607

2
DATE : Sep 09/94 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 22/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

(c) Effectivity by MSN and Kit/Configuration

The kits and configurations applicable to these 

at the end of this list:

0252 0284 0294 0301 0307 0312 0317 0321 0336 034

0351 0354 0358 0361 0365 0368 0371 0377 0380 03

0395 0398 0401 0405 0408 0411 0414 0417

NOTE (01) For each Kit, read Config. 01 or 02.

The kits and configurations applicable to these 

at the end of this list:

0423 0459-0466 0469-0471 0474 0477 0479 0505-05

0529-0530 0532-0533 0536 0540 0543 0546 0553-05

SUD 0252

SVA 0284 0294 0301 0307 0312 0317 0321 0

0351

TAR 0505 0558 0563

THA 0368 0371 0377 0384 0395 0398 0464 0

0577 0628 0629 0635 0681 0705 0782 0

0787

KIT No. QTY PER A/C CONFIGURATION

576049A01R05 1 01

02

576049A03R09 1 01

02

576049A04R06 1 01

02

576049A06R04 1 01

02

576049A08R01 1 01

02

576049A09R00 1 01

02

576049A10R00 1 01

02

3
DATE : Sep 09/94 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 22/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

NOTE (01) For each Kit, read Config. 01 or 02.

The kits and configurations applicable to these 

at the end of this list:

0797 0799-0804

The kits and configurations applicable to these 

at the end of this list:

0726-0750 0752-0764 0766-0775 0777-0794

576049A02R06 1 01

02

576049A03R09 1 01

02

576049A05R06 1 01

02

576049A06R04 1 01

02

576049A08R01 1 01

02

576049A09R00 1 01

02

576049A10R00 1 01

02

KIT No. QTY PER A/C CONFIGURATION

576049A02R06 1 03

576049A03R09 1 03

576049A05R06 1 03

576049A06R04 1 03

576049A09R00 1 03

KIT No. QTY PER A/C CONFIGURATION

576049A07R03 1 04

4
DATE : Sep 09/94 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 22/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

NOTE : When the airplane model designation is o

changed from one of the following simplif

model designation B4-600, the value quote

be revised. In such a case, AIRBUS must b

implement changes.

NOTE : Kit 576049A01R05 : Hole H with crack.

- valid aircraft MSN 0252 thru 0417 (with

Bulletin No. A300-57-6050 embodied).

NOTE : Kit 576049A02R06 : Hole H with crack.

- Valid aircraft MSN 0420 thru 0725 (with

Bulletin No. A300-57-6050 embodied).

- Valid aircraft MSN 0797 and subsequent 

10155S20321 embodied in production line)

NOTE : Kit 576049A03R09 : Hole I with crack.

- Valid aircraft MSN 0252 thru 0725 (with

Bulletin No. A300-57-6050 embodied).

- Valid aircraft MSN 0797 and subsequent 

10155S20321 embodied in production line)

NOTE : Kit 576049A04R06 : Holes H and I without 

- Valid aircraft MSN 0252 thru 0417 (with

Bulletin No. A300-57-6050 embodied).

NOTE : Kit 576049A05R06 : Holes H and I without 

- Valid aircraft MSN 0420 thru 0725 (with

Bulletin No. A300-57-6050 embodied).

- Valid aircraft MSN 0797 and subsequent 

10155S20321 embodied in production line)

01 

02 *

03 *

04 

5
DATE : Sep 09/94 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 22/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

NOTE : Kit 576049A07R03 : Holes H, I, K, L, M, N

X with or without crack.

- Valid aircraft MSN 0726 thru 0794 (Mod

10155S20321 partly embodied in production 

NOTE : Kit 576049A08R01 : Holes H, I, K, L, M, N 

crack.

- Valid aircraft MSN 0252 thru 0725 (with 

Bulletin No. A300-57-6050 embodied).

NOTE : Kit 576049A09R00 : Holes U, V, W, X, Y wi

crack.

- Valid aircraft MSN 0252 thru 0725 (with

Bulletin No. A300-57-6050 embodied).

- valid aircraft MSN 0797 and subsequent 

10155S20321 embodied in production line)

NOTE : Kit 576049A10R00 : Holes U, V, W, X, Y wi

- Valid aircraft MSN 0252 thru 0725 (with 

Bulletin No. A300-57-6050 embodied).

NOTE : Config. 01 and 02 concerns B4/600 type, B

B4-605R, B4-620, B4-622, B4-622R, C4-605R

models.

NOTE : Config. 03 and 04 concerns B4/600 type, 

B4-605R, C4-605R/F, F4-605R models.

(3) Spares

None

B. CONCURRENT REQUIREMENTS

None

6
DATE : Sep 09/94 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 22/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Cracks if undetected can increase in magnitude in rea

panel, thus reducing the residual strength capacity o

structure and requiring and extensive structural repa

The in-service experience from the application of ins

A300 and A300-600 fleets shows that:

— Cracks have been found before reaching the thresho

— Cracks have been found in other holes (basically ho

were inspected) during accomplishment of modificat

Bulletins No. A300-53-0298 and A300-57-6050.

Revision No.03 of this Service Bulletin takes this n

account.

From Revision No.03 of this SB, further in service ex

shown that cracks have been found in other holes tha

K, L, M and N. This is why Revision No.06 request to 

holes U, V, W, X and Y in order to take these new fi

account.

(2) Objective/Action

The aim of this Service Bulletin is to call for eddy 

inspection of holes H, I, K, L, M, N and U, V, W, X, 

internal angles of wing center box.

(3) Advantages

This inspection will make it possible to detect crac

at an early stage, thus avoiding an extensive repair

Accomplishment of Service Bulletin No. A300-57-6069 

requirement of inspection of holes H and I of the co

fitting defined in this Service Bulletin and cancels 

requirement of inspection of the rear spar and bottom 

junction with fuselage defined in Service Bulletin No

A300-57-6086.

(4) Operational/Maintenance Consequences

None

D. DESCRIPTION

To accomplish this Service Bulletin it is necessary to :

7
DATE : Sep 09/94 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 22/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

— Performing rotating probe inspection.

— Reinstalling fasteners.

— Applying PR sealant.

— Test.

— Close-up.

E. COMPLIANCE

(1) Classification

Mandatory

(2) Accomplishment Timescale

Accomplishment of this Service Bulletin has been rend

by the issue of an Airworthiness Directive (AD) publ

European Aviation Safety Agency (EASA). The AD must 

reference document for the mandatory accomplishment t

This Service Bulletin is mandatory at the following t

intervals, whichever occurs first.

HOLES H, I, K, L, M, N, U, V, W, X, Y

AFT: Average Flight Time

CONFIG.No. THRESHOLD THRESHOLD INTERVAL 

** Flight

Cycles

Flight Hours Flight

Cycles

01 10400 22450 4500 

02 14200* 30650 4500 

03 14200 30650 4500 

01AFT<=1,5FH/FC 11250 16850 4850 

02AFT<=1,5FH/FC 15350* 23000 4850 

03AFT<=1,5FH/FC 15350 23000 4850 

8
DATE : Sep 09/94 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 22/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

HOLES H, I, K, L, M, N, U, V, W, X, Y

AFT: Average Flight Time

Grace Period:

— Where A/C are between 1400 FC/3500 FH less than thr

exceeded the threshold by less than 1900 FC/4600 F

first inspection is to be performed within 1400 FC/

receipt of this Service Bulletin.

— For A/C which have exceeded the threshold by more t

FC/4600 FH flights, the first inspection is to be 

within 700 FC/1700 FH after receipt of this Service 

NOTE : The number of touch and go flights can be neg

they are less than five percent of the total 

flights between two consecutive inspections.

When the percentage of touch and go flights i

five percent of total number of flights betwee

consecutive inspections, each touch and go fl

five percent has to be counted as a flight cyc

A touch and go is a landing in which an airpla

runway and does not come to a full stop prior 

an additional flight.

F. APPROVAL

Approved under EASA Design Organisation Approval No. EASA 

If an aircraft listed in the effectivity has a modificatio

embodied that is not of AIRBUS origin, and which affects 

this Service Bulletin, the operator is responsible for ob

approval by its airworthiness authority for any adaptatio

before incorporation of the Service Bulletin.

CONFIG.No. THRESHOLD THRESHOLD INTERVAL 

Flight

Cycles

Flight Hours Flight

Cycles

04 12300 26550 4500 

04AFT<=1,5FH/FC 13300 19950 4850 

9
DATE : Sep 09/94 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 22/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

and general administration work are also not included.

Inspection LH and RH sides, Config.01 or 02 or 03 or 04

Rework the hole

Rework the fitting

H. WEIGHT AND BALANCE

Not changed

I. ELECTRICAL LOAD DATA

Not changed

J. REFERENCES

Get access 

Rotating probe inspection 

Test 

Close-up 

TOTAL MANHOURS 

ELAPSED TIME (HOURS) 

Rework for one hole 

TOTAL MANHOURS 

ELAPSED TIME (HOURS) 

Cut out fitting (for one

fitting)

TOTAL MANHOURS 

ELAPSED TIME (HOURS) 

Aircraft Maintenance Manual (AMM) : 06-41-53 20-21-12 

24-41-00 28-00-00 

28-11-00 28-11-29 

28-21-00 28-22-00 

29-14-00 29-25-00 

29-33-00 33-42-00 

Consumable Material List (CML)

10
DATE : Sep 09/94 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 22/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

g () , , 

B

Maintenance Review Board Document (MRB) Section 5

Service Bulletin No. A300-28-6028

Service Bulletin No. A300-57-6050

Service Bulletin No. A300-57-6069

Service Bulletin No. A300-57-6086

Appendix 1

K. PUBLICATIONS AFFECTED

None

L. INTERCHANGEABILITY/MIXABILITY

None

11
DATE : Sep 09/94 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 22/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

This Page Intentionally Left Blank

12
DATE : Sep 09/94 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 22/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

of this Service Bulletin. The address is :

Airbus Spares Support and Services

Weg beim Jaeger 150

D-22335 Hamburg

Germany

For ordering by internet: http://spa

For ordering by fax: +49 40 50 76 25 

(2) Price and Availability

Kit 576049A01R05

Cost : 727.00 US Dollars

Availability : 90 calendar days from receipt of orde

The Kit availability given above is the standard lead 

date of your purchase order. If you require the Kit(

time, please include a retrofit planning schedule wit

so that we can try to comply with your requirements.

The sales terms (costs and availability) are estimat

to economic conditions at the issue date of the Serv

Kit 576049A02R06

Cost : 2,080.00 US Dollars

Availability : 90 calendar days from receipt of orde

The Kit availability given above is the standard lead 

date of your purchase order. If you require the Kit(

time, please include a retrofit planning schedule wit

so that we can try to comply with your requirements.

The sales terms (costs and availability) are estimat

to economic conditions at the issue date of the Serv

Kit 576049A03R09

Cost : 2,998.00 US Dollars

Availability : 150 calendar days from receipt of orde

13
DATE : Sep 09/94 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 22/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Kit 576049A04R06

Cost : 1,140.00 US Dollars

Availability : 120 calendar days from receipt of orde

The Kit availability given above is the standard lead 

date of your purchase order. If you require the Kit(

time, please include a retrofit planning schedule wit

so that we can try to comply with your requirements.

The sales terms (costs and availability) are estimat

to economic conditions at the issue date of the Serv

Kit 576049A05R06

Cost : 1,270.00 US Dollars

Availability : 150 calendar days from receipt of orde

The Kit availability given above is the standard lead 

date of your purchase order. If you require the Kit(

time, please include a retrofit planning schedule wit

so that we can try to comply with your requirements.

The sales terms (costs and availability) are estimat

to economic conditions at the issue date of the Serv

Kit 576049A06R04

Cost : 2,090.00 US Dollars

Availability : 120 calendar days from receipt of orde

The Kit availability given above is the standard lead 

date of your purchase order. If you require the Kit(

time, please include a retrofit planning schedule wit

so that we can try to comply with your requirements.

The sales terms (costs and availability) are estimat

to economic conditions at the issue date of the Serv

Kit 576049A07R03

Cost : 5,780.00 US Dollars

Availability : 120 calendar days from receipt of orde

14
DATE : Sep 09/94 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 22/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Kit 576049A08R01

Cost : 1,600.00 US Dollars

Availability : 120 calendar days from receipt of orde

The Kit availability given above is the standard lead 

date of your purchase order. If you require the Kit(

time, please include a retrofit planning schedule wit

so that we can try to comply with your requirements.

The sales terms (costs and availability) are estimat

to economic conditions at the issue date of the Serv

Kit 576049A09R00

Cost : 4,198.00 US Dollars

Availability : 99 calendar days from receipt of orde

The Kit availability given above is the standard lead 

date of your purchase order. If you require the Kit(

time, please include a retrofit planning schedule wit

so that we can try to comply with your requirements.

Kit 576049A10R00

Cost : 3,602.00 US Dollars

Availability : 99 calendar days from receipt of orde

The Kit availability given above is the standard lead 

date of your purchase order. If you require the Kit(

time, please include a retrofit planning schedule wit

so that we can try to comply with your requirements.

B. INDUSTRY SUPPORT INFORMATION

Airbus will not provide industrial support for accomplishm

Service Bulletin.

C. LIST OF COMPONENTS

Kit 576049A01R05

15
DATE : Sep 09/94 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 22/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

NOTE : Refer to the AIRBUS Standards Manual (SM) if you f

numbers of hardware components in the related kit(

cannot identify in the LIST OF COMPONENTS of this 

Bulletin. The SM will give you the correct part num

number relationship.

Kit 576049A02R06

NOTE : Refer to the AIRBUS Standards Manual (SM) if you f

numbers of hardware components in the related kit(

cannot identify in the LIST OF COMPONENTS of this 

Bulletin. The SM will give you the correct part num

number relationship.

Kit 576049A03R09

ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. 

2 ASNA0093-7-36 2 Bolt

3 ASNA0093-8-36 2 Bolt

42 NAS1726-7E 2 Nut

43 NAS1726-8E 2 Nut

ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. 

7 NSA5351V8-28 2 Bolt

16 NSA5357-8-28 2 Pin

31 NSA5359-8-28 2 Bolt

36 NSA5050-8 2 Nut

38 NSA5059-4 2 Nut

39 NSA5059-5 4 Nut

40 NSA5060-4 1 Nut

43 NAS1726-8E 2 Nut

47 MS24665-152 6 Pin

48 MS24665-153 1 Pin

49 NSA5368PD616B 5 Washer

50 NSA5368PD716B 10 Washer

51 NSA5368PD816B 10 Washer

52 NSA5368PD916B 2 Washer

16
DATE : Sep 09/94 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 22/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

NOTE : Refer to the AIRBUS Standards Manual (SM) if you f

numbers of hardware components in the related kit(

cannot identify in the LIST OF COMPONENTS of this 

Bulletin. The SM will give you the correct part num

number relationship.

Kit 576049A05R06

NOTE : Refer to the AIRBUS Standards Manual (SM) if you f

numbers of hardware components in the related kit(

cannot identify in the LIST OF COMPONENTS of this 

Bulletin. The SM will give you the correct part num

number relationship.

Kit 576049A06R04

ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. 

4 NSA5351V6-36 2 Bolt

5 NSA5351V7-36 2 Bolt

9 NSA5351V8-34 2 Bolt

10 NSA5351V8-36 2 Bolt

19 NSA5357-8-34 2 Bolt

30 NSA5359-8-34 2 Bolt

34 NSA5050-6 2 Nut

35 NSA5050-7 2 Nut

36 NSA5050-8 4 Nut

43 NAS1726-8E 4 Nut

ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. 

1 ASNA0093-6-36 2 Bolt

2 ASNA0093-7-36 2 Bolt

3 ASNA0093-8-36 2 Bolt

9 NSA5351V8-34 2 Bolt

19 NSA5357-8-34 2 Bolt

30 NSA5359-8-34 2 Bolt

36 NSA5050-8 2 Nut

41 NAS1726-6E 2 Nut

42 NAS1726-7E 2 Nut

43 NAS1726-8E 6 Nut

17
DATE : Sep 09/94 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 22/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

NOTE : Refer to the AIRBUS Standards Manual (SM) if you f

numbers of hardware components in the related kit(

cannot identify in the LIST OF COMPONENTS of this 

Bulletin. The SM will give you the correct part num

number relationship.

Kit 576049A07R03

21 NSA5359-8-25 2 Pin

29 NSA5359-8-31 2 Bolt

32 NSA5351V8-31 2 Bolt

36 NSA5050-8 8 Nut

37 NSA5050-9 4 Nut

43 NAS1726-8E 4 Nut

ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. 

4 NSA5351V6-36 2 Bolt

5 NSA5351V7-36 2 Bolt

7 NSA5351V8-28 2 Bolt

10 NSA5351V8-36 2 Bolt

11 NSA5351V9-25 2 Bolt

12 NSA5351V9-30 2 Bolt

13 NSA5357-8-25 10 Bolt

14 NSA5357-8-26 2 Pin

15 NSA5357-8-27 2 Pin

16 NSA5357-8-28 2 Pin

17 NSA5357-8-30 2 Bolt

18 NSA5357-8-31 2 Bolt

19 NSA5357-8-34 2 Bolt

21 NSA5359-8-25 10 Pin

26 NSA5359-8-26 2 Pin

27 NSA5359-8-27 2 Pin

28 NSA5359-8-30 2 Bolt

29 NSA5359-8-31 2 Bolt

30 NSA5359-8-34 2 Bolt

31 NSA5359-8-28 2 Bolt

34 NSA5050-6 2 Nut

35 NSA5050-7 2 Nut

36 NSA5050-8 4 Nut

18
DATE : Sep 09/94 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 22/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

NOTE : Refer to the AIRBUS Standards Manual (SM) if you f

numbers of hardware components in the related kit(

cannot identify in the LIST OF COMPONENTS of this 

Bulletin. The SM will give you the correct part num

number relationship.

Kit 576049A08R01

NOTE : Refer to the AIRBUS Standards Manual (SM) if you f

numbers of hardware components in the related kit(

cannot identify in the LIST OF COMPONENTS of this 

Bulletin. The SM will give you the correct part num

number relationship.

Kit 576049A09R00

47 MS24665-152 6 Pin

48 MS24665-153 1 Pin

49 NSA5368PD616B 5 Washer

50 NSA5368PD716B 10 Washer

51 NSA5368PD816B 10 Washer

52 NSA5368PD916B 2 Washer

ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. 

20 NSA5359-6-36 2 Bolt

21 NSA5359-8-25 4 Pin

28 NSA5359-8-30 2 Bolt

29 NSA5359-8-31 2 Bolt

30 NSA5359-8-34 2 Bolt

41 NAS1726-6E 2 Nut

43 NAS1726-8E 10 Nut

ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. 

6 NSA5351V8-25 6 Bolt

13 NSA5357-8-25 6 Bolt

14 NSA5357-8-26 2 Pin

15 NSA5357-8-27 2 Pin

22 NSA5351V8-26 2 Bolt

23 NSA5351V8-27 2 Bolt

19
DATE : Sep 09/94 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 22/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

y 

Bulletin. The SM will give you the correct part num

number relationship.

Kit 576049A10R00

NOTE : Refer to the AIRBUS Standards Manual (SM) if you f

numbers of hardware components in the related kit(

cannot identify in the LIST OF COMPONENTS of this 

Bulletin. The SM will give you the correct part num

number relationship.

D. LIST OF MATERIALS — OPERATOR SUPPLIED

(1) Consumable Materials

(2) Components

None

E. PARTS TO BE RE—IDENTIFIED BY THE OPERATOR

None

ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. 

21 NSA5359-8-25 6 Pin

26 NSA5359-8-26 2 Pin

27 NSA5359-8-27 2 Pin

43 NAS1726-8E 10 Nut

DESCRIPTION REFERENCE TO CML

MAT. No.

QTY PER A/C 

Fuel Tank Sealant

Polysulfide

09-001 As required

Corrosion Interfay Sealant 09-005 As required

Solvant General Purpose 11-026 As required

Chemical Conversion Coating

Yellow Aluminum

13-002 As required

Anti-Corrosion Primer

(Epoxy-Imprvdadhesion)

16-006 As required

External Top Coat

(Polyurethane)

16-018 As required

20
DATE : Sep 09/94 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 22/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

G. SPECIAL TOOLS

None

21
DATE : Sep 09/94 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 22/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

This Page Intentionally Left Blank

22
DATE : Sep 09/94 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 22/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY 

MECHANICALLY SERVICEABLE). WHEN YOU DO MAINTENAN

REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICA

COMPONENTS AND THE WORK AREA AS CLEAN AS POSSIBL

PUT PROTECTION, SUCH AS PLASTIC SHEETING, CLOTH

NECESSARY ON WIRING AND COMPONENTS.

REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIA

CONTAMINATION.

THESE PRECAUTIONS WILL DECREASE THE RISK OF CONT

DAMAGE TO THE ELECTRICAL WIRING INSTALLATION.

IN CASE OF CONTAMINATION REFER TO ESPM 20-55-00

(1) Preparation

(a) Electrically ground the aircraft (Refer to AMM 

block 301).

(b) Put the access platforms in position.

(c) Defuel center fuel tank (Refer to AMM 28-25-00 

301).

(d) Perform degassing of center fuel tank (Refer to 

Page block 301) and (Refer to AMM 28-10-00 Page 

NOTE : Make certain that safety precautions rega

to, and working in, center fuel tank are strict

(e) Open the access doors 147AZ and 148AZ (Refer to 

and (Refer to AMM 28-11-29 Page block 401).

(f) Open, safety and tag these circuit breakers:

PANEL DESIGNATION FIN LOCA

132VU LIGHTING-EXRERIOR LT-LAND L

SUPPLY

1LB N 80

132VU LIGHTING-EXRERIOR LT-LAND R

SUPPLY

2LB M 78

132VU LIGHTING-EXRERIOR LT-LAND L

SUPPLY

3LB M 81

132VU LIGHTING-EXRERIOR LT-LAND R CTL 4LB M 77

23
DATE : Sep 09/94 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 22/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

(2) Standard Practices

(a) For inspection

1 For the specification of the material number

refer to CML.

2 To clean the surface to be sealed with Solva

Purpose (Mat No. 11-026) .

3 Do the sealing processes (Refer to SRM 51-76

4 Torque the standard threaded fasteners (Refe

20-21-12) and (Refer to SRM 51-43-00).

5 For alternative and substitute fasteners, (Re

51-40-32).

6 Install the fasteners with Corrosion Interfay 

No. 09-005) and encapsulate exposed parts of 

with Fuel Tank Sealant Polysulfide (Mat No

(b) For repair

1 Drill fastener holes (Refer to SRM 51-40-40)

2 For oversized fasteners (Refer to SRM 51-40-

3 For fastener spacing and margin data (Refer t

51-40-50).

4 For alternative and substitute fasteners, (Re

51-40-32).

5 To countersink data (Refer to SRM 51-40-47).

133VU ENG1/PUMP CTL/B 31GJ 331/

133VU PTU CTL/G/Y 6GL 332/

133VU ENG2/PUMP CTL/Y 1GD 332/

133VU RAT/TEST 1GF 331/

133VU ACCU PRESS/CTL &/CARGO DOOR/PUMP 7GX 333/

101VU ELEC/HYD/PUMP 23GX GEN2

133VU RSVR/WARN 1GQ 333/

24
DATE : Sep 09/94 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 22/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

(1) Get access to the inspection area.

Refer to figures 4 , 5 , 6 , 7

(a) Removal of LH hydraulic panel.

1 Remove Fairings (refer to figure 4 )

2 In zone 542, disconnect plugs 43QA-A and 49QA

3 In zone 571, remove ties and disconnect plugs 

11QQ-A,24GQ-A, 33GR-A, 51QA-A, 57QA-A, 1935VC

and ground connections 536VN and 538VN.

NOTE : Plugs 11QQ-A and 12QQ-A:

Available only on A/C with Mod. No. 08

(Service Bulletin No. A300-28-6028 ).

4 Remove hydraulic panel (refer to figure 5 )

(b) Removal of RAT (Ram Air Turbine) panel

1 Remove fairings (refer to figure 4 )

2 Fairings Item (6

4 Inserts Item (6

2 Bushes Item (6

2 Fairings Item (6

2 Bolts Item (6

2 Bolts Item (6

4 Nuts Item (6

1 Hydraulic panel

assy

Item (5

6 Guides Item (6

6 Bolts Item (6

1 Bolt Item (6

2 Bolts Item (7

2 Washers Item (7

1 Washer Item (7

1 Nut Item (3

2 Nut Item (3

3 Cotter pins Item (4

25
DATE : Sep 09/94 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 22/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

2 Remove hydraulic lines

CAUTION: PLUG/CAP PORTS AND ALL OPEN LINE END

— Return filter line

— Pressurization line

— Overflow line

— Return line

3 Remove adjustable rod/crank link of RAT (refe

)

WARNING : BEFORE PROCEEDING WITH ANY WORK ON 

CERTAIN THAT UPLOCK UNIT ACTUATING 

PIN IS CORRECTLY INSERTED.

4 In zone 671, remove ties and disconnect plug

12QQ-A, 52QA-A, 58QA-A, 1936VC-A, 1983VC-A.

5 Remove RAT panel, refer to figure 7

(2) For the inspection area and holes location, refer to 

sheets 1 and 2 .

4 Nuts Item (6

1 Bolt Item (7

1 Nut Item (4

1 Sleeve Item (7

1 Washer Item (7

1 Cotter pin Item (4

1 Hydraulic panel

assy

Item (5

3 Guides Item (6

3 Guides Item (7

6 Bolts Item (6

1 Bolt Item (6

2 Bolts Item (7

2 Washers Item (7

1 Washer Item (7

1 Nut Item (3

2 Nuts Item (3

3 Cotter pin Item (4

26
DATE : Sep 09/94 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 22/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Refer to figure 3 , sheets 1 thru 9 .

(4) For the Inspection Report, refer to Appendix 01 .

C. REPAIR

(1) Replace fasteners, hole H (config.No 01 or 02 or 03)

Refer to figure 8 and figure 9 .

NOTE : During the installation, if the fasteners are 

+1.6mm(0.063in.), it is possible to add one wa

(for oversize bolt) with a new nut the refere

must be the same as the reference of removed 

(a) Kit 576049A04R06

(b) Kit 576049A05R06

(c) Kit 576049A08R01

(d) Kit 576049A01R05

(e) Kit 576049A02R06

2 Bolt NSA5351V6-36 Item 4

2 Bolt NSA5351V7-36 Item 5

2 Bolt NSA5351V8-36 Item 10

2 Nut NSA5050-6 Item 34

2 Nut NSA5050-7 Item 35

2 Nut NSA5050-8 Item 36

2 Bolt ASNA0093-6-36 Item 1

2 Bolt ASNA0093-7-36 Item 2

2 Bolt ASNA0093-8-36 Item 3

2 Nut NAS1726-6E Item 41

2 Nut NAS1726-7E Item 42

2 Nut NAS1726-8E Item 43

2 Bolt NSA5359-6-36 Item 20

2 Nut NAS1726-6E Item 41

2 Bolt NSA5351V7-36 Item 5

2 Bolt NSA5351V8-36 Item 10

2 Nut NSA5050-7 Item 35

2 Nut NSA5050-8 Item 36

27
DATE : Sep 09/94 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 22/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

gg

NOTE : During the installation, if the fasteners are 

+1.6mm(0.063in.), it is possible to add one wa

(for oversize bolt) with a new nut the refere

must be the same as the reference of removed 

(a) Kit 576049A04R06

(b) Kit 576049A08R01

(c) Kit 576049A04R06

(d) Kit 576049A03R09

(3) Replace fasteners, holes K and N (config.No 01 or 02 

Refer to figure 8 , figure 11 and figure 14 .

NOTE : During the installation, if the fasteners are 

+1.6mm(0.063in.), it is possible to add one wa

(for oversize bolt) with a new nut the refere

must be the same as the reference of removed 

(a) Kit 576049A06R04

2 Bolt NSA5351V8-34 Item 9

2 Bolt NSA5357-8-34 Item 19

2 Nut NSA5050-8 Item 36

2 Nut NAS1726-8E Item 43

2 Bolt NSA5359-8-34 Item 30

2 Nut NAS1726-8E Item 43

2 Bolt NSA5359-8-34 Item 30

2 Nut NAS1726-8E Item 43

2 Bolt NSA5351V8-28 Item 7

2 Bolt NSA5357-8-28 Item 16

2 Bolt NSA5359-8-28 Item 31

2 Nut NSA5050-8 Item 36

2 Nut NAS1726-8E Item 43

5 Washer NSA5368PD616B Item 49

10 Washer NSA5368PD716B Item 50

10 Washer NSA5368PD816B Item 51

2 Washer NSA5368PD916B Item 52

28
DATE : Sep 09/94 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 22/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

(c) Kit 576049A06R04

(4) Replace fasteners, holes L and M (config.No 01 or 02 

Refer to figure 8 , figure 11 and figure 14 .

NOTE : During the installation, if the fasteners are 

+1.6mm(0.063in.), it is possible to add one wa

(for oversize bolt) with a new nut the refere

must be the same as the reference of removed 

(a) Kit 576049A06R04

(b) Kit 576049A08R01

(c) Kit 576049A06R04

(5) Replace the fasteners of the holes U, V, W, X and Y 

or 02 or 03).

Refer to figure 8 , figure 12 , sheets 1 and 2 .

NOTE : During the installation, if the fasteners are 

+1.6mm(0.063in.), it is possible to add one wa

(for oversize bolt) with a new nut the refere

must be the same as the reference of removed 

(a) Kit 576049A09R00

2 Bolt NSA5359-8-30 Item 28

4 Nut NAS1726-8E Item 43

2 Bolt NSA5351V9-25 Item 11

2 Bolt NSA5351V9-30 Item 12

4 Nut NSA5050-9 Item 37

2 Bolt NSA5351V8-25 Item 6

2 Bolt NSA5351V8-31 Item 32

4 Nut NSA5050-8 Item 36

2 Bolt NSA5359-8-25 Item 21

2 Bolt NSA5359-8-31 Item 29

4 Nut NAS1726-8E Item 43

2 Bolt NSA5359-8-31 Item 29

2 Bolt NSA5359-8-25 Item 21

4 Nut NAS1726-8E Item 43

29
DATE : Sep 09/94 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 22/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

(b) Kit 576049A10R00

(6) Replace fasteners, hole H (config. No.04).

Refer to figure 8 and figure 13

NOTE : During the installation, if the fasteners are 

+1.6mm(0.063in.), it is possible to add one wa

(for oversize bolt) with a new nut the refere

must be the same as the reference of removed 

(a) Kit 576049A07R03

(b) Kit 576049A07R03

(7) Replace fasteners, hole I (config. No.04).

Refer to figure 8 and figure 13 .

NOTE : During the installation, if the fasteners are 

+1.6mm(0.063in.), it is possible to add one wa

(for oversize bolt) with a new nut the refere

must be the same as the reference of removed 

(a) Kit 576049A07R03

10 Nut NSA50508 Item 36

10 Nut NAS1726-8E Item 43

6 Bolt NSA5359-8-25 Item 21

2 Bolt NSA5359-8-26 Item 26

2 Bolt NSA5359-8-27 Item 27

10 Nut NAS1726-8E Item 43

2 Bolt NSA5351V6-36 Item 4

2 Bolt NSA5351V7-36 Item 5

2 Bolt NSA5351V8-36 Item 10

2 Nut NSA5050-6 Item 34

2 Nut NSA5050-7 Item 35

2 Nut NSA5050-8 Item 36

2 Bolt NSA5351V7-36 Item 5

2 Bolt NSA5351V8-36 Item 10

2 Nut NSA5050-7 Item 35

2 Nut NSA5050-8 Item 36

2 Bolt NSA5357-8-34 Item 19

2 Nut NAS1726-8E Item 43

30
DATE : Sep 09/94 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 22/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

(8) Replace fasteners, holes K and N (config. No.04).

Refer to figure 8 and figure 13 .

NOTE : During the installation, if the fasteners are 

+1.6mm(0.063in.), it is possible to add one wa

(for oversize bolt) with a new nut the refere

must be the same as the reference of removed 

(a) Kit 576049A07R03

(b) Kit 576049A07R03

(9) Replace fasteners, holes L and M (config. No.04).

Refer to figure 8 and figure 13 .

NOTE : During the installation, if the fasteners are 

+1.6mm(0.063in.), it is possible to add one wa

(for oversize bolt) with a new nut the refere

must be the same as the reference of removed 

(a) Kit 576049A07R03

(b) Kit 576049A07R03

2 Bolt NSA5357-8-28 Item 16

2 Bolt NSA5359-8-28 Item 31

2 Nut NSA5050-8 Item 36

2 Nut NAS1726-8E Item 43

2 Bolt NSA5357-8-25 Item 13

2 Bolt NSA5359-8-25 Item 21

2 Bolt NSA5357-8-30 Item 17

2 Bolt NSA5359-8-30 Item 28

4 Nut NAS1726-8E Item 43

2 Bolt NSA5351V9-25 Item 11

2 Bolt NSA5351V9-30 Item 12

4 Nut NSA5050-9 Item 37

2 Bolt NSA5357-8-25 Item 13

2 Bolt NSA5359-8-25 Item 21

2 Bolt NSA5357-8-31 Item 18

2 Bolt NSA5359-8-31 Item 29

4 Nut NAS1726-8E Item 43

31
DATE : Sep 09/94 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 22/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

NOTE : During the installation, if the fasteners are 

+1.6mm(0.063in.), it is possible to add one wa

(for oversize bolt) with a new nut the refere

must be the same as the reference of removed 

(a) Kit 576049A07R03

(11) Install RAT panel assembly

Refer to figures 6 and 7

(a) Install panel (Refer to figure 7)

NOTE : Items (58), (67), (73), (68), (69), (70)

were retained at removal.

(b) In zone 671, install ties and connect plugs 12Q

52QA-A, 58QA-A, 1936VC-A, 1938VC-A.

(c) Install adjustable rod/crank link of RAT (refer 

6 Bolt NSA5357-8-25 Item 13

6 Bolt NSA5359-8-25 Item 21

2 Bolt NSA5357-8-26 Item 14

2 Bolt NSA5359-8-26 Item 26

2 Bolt NSA5357-8-27 Item 15

2 Bolt NSA5359-8-27 Item 27

10 Nut NAS1726-8E Item 43

1 Panel assy Item (5

3 Guides Item (6

3 Guides Item (7

6 Bolts Item (6

1 Bolt Item (6

2 Bolts Item (7

2 Washer Item (7

1 Washer Item (7

1 Nut NSA5059-4 Item 38

2 Nuts NSA5059-5 Item 39

3 Cotter pin MS24665-152 Item 47

1 Bolt Item (7

1 Nut NSA5060-4 Item 40

32
DATE : Sep 09/94 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 22/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

(d) Install hydraulic lines:

— Return filter line

— Pressurization line

— Overflow line

— Return line.

(12) Installation of LH hydraulic panel

Refer to figure 5

(a) Install hydraulic panel

NOTE : Items (59), (67), (68), (69), (70), (71)

retained at removal.

(b) In zone 571, install ties and connect plugs 3GH

11QQ-A, 24GQ-A, 33GR-A, 51QA-A, 57QA-A, 1935VC-A

ground connections 536VN and 538VN.

(13) Install fairings, on LH and RH sides.

Refer to figure 4

(a) Install on LH side

1 Hydraulic panel

assy

Item (5

6 Guides Item (6

6 Bolt Item (6

1 Bolt Item (6

2 Bolt Item (7

2 Washer Item (7

1 Washer Item (7

1 Nut NSA5059-4 Item 38

2 Nuts NSA5059-5 Item 39

3 Cotter pin MS24665-152 Item 47

2 Fairing Item (6

4 Insert Item (6

2 Bushes Item (6

2 Fairing Item (6

2 Bolt Item (6

33
DATE : Sep 09/94 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 22/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

NOTE : Items (60), (61), (62), (63), (64), (65)

retained at removal.

(c) In zone 542, connect plugs 43QA-A and 49QA-A.

D. TEST

(1) Job set-up

(a) Connect electrical ground power unit and energiz

electrical network and make certain that electro

ventilated (Refer to AMM 24-41-00 Page block 30

(b) Close access doors 147AZ, 148AZ (Refer to AMM 2

block 401).

(c) Refuel center tank (Refer to AMM 28-25-00 Page 

(2) Test

(a) Perform operational test of landing lights (Refe

33-42-00 Page block 501).

(b) Perform functional test of hydraulic fluid tank 

system (Refer to AMM 29-14-00 Page block 501).

(c) Perform operational test of hydraulic fluid tem

indicating system (Refer to AMM 29-33-00 Page b

(d) Perform adjustment of rod/crank of RAT (Refer to 

Page block 501).

(e) Perform functional test of yellow auxiliary powe

to AMM 29-25-00 Page block 501).

(f) Perform functional test of hydraulic fluid indi

(Refer to AMM 29-31-00 Page block 501).

2 Fairing Item (6

4 Insert Item (6

2 Bushes Item (6

2 Fairing Item (6

2 Bolt Item (6

2 Bolt Item (6

4 Nut Item (6

34
DATE : Sep 09/94 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 22/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

(j) Perform test procedure of fuel pump water scave

inner tank, described below.

NOTE (01) This test is only required on aircraft 

Mod. No.08679, No.08680 or Service Bul

A300-28-6028 accomplished.

NOTE (02) Plugs 11QQ-A and 12QQ-A: available A/C 

Mod. No.08679, No.08680 or Service Bul

A300-28-6028 accomplished.

(k) Open, safety and tag these circuit breakers:

(l) Make sure that these circuit breakers are closed

— Energize the aircraft electrical circuits (Ref

24-41-00 Page block 301).

— On the panel 9VU, make sure that the ENG1 and 

control levers are in OFF position.

— Refuel the aircraft to get a minimum fuel qua

1500 kgs (3300 lbs) and 2000 kgs (4400 lbs) (

28-11-41 Page block 501).

PANEL DESIGNATION FIN LOCA

101VU FUEL/L INNER TK/PUMP 2/SUPPLY 1QA ESS1

101VU FUEL/R INNER TK/PUMP 1/SUPPLY 2QA ESS1

101VU FUEL/L INNER TK/PUMP 1/SUPPLY 7QA GEN2

101VU FUEL/R INNER TK/PUMP 2/SUPPLY 8QA GEN2

101VU FUEL/CTR TK/L PUMP SUPPLY 99BA ESS/

101VU FUEL/CTR TK/R PUMP SUPPLY 100QA GEN2

132VU SCAVENGE SYSTEM/PUMP/INNER L 1QQ 325/

132VU SCAVENGE SYSTEM/PUMP/INNER R 2QQ 325/

132VU SCAVENGE SYSTEM/PUMP/TT 3QQ 325/

PANEL DESIGNATION FIN LOCA

132VU SCAVENGE SYSTEM/PUMP/CONTROL 13QQ 325/

132VU FUEL/AUTO FEED CTL 65QA 323M 

132VU LIGHTING/MAINT PANEL/ANN & MFA 1WB 324/

132VU LIGHTING/MAINT PANEL/ANN & MFA 22WB 324/

35
DATE : Sep 09/94 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 22/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

— Do this test:

ACTION RESULT

1. On the maintenance panel 472VU:

— Put the ANN LT switch in the TEST

position.

— The fault light on the 

system annunciator com

— Put the ANN LT switch in the READ

position.

— Push in the MFA RESET switch. — The fault light on the 

system annunciator goe

2. On the overhead panel 430VU:

— Press (in) all the INR TK pump

pushbutton switshes (p/bsw).

— The OFF lights on the 

p/bsw go OFF.

— Press (in) both the CTR TK PUMP

p/bsw.

— The OFF lights on both 

PUMP p/bsw go OFF.

3. On the maintenance panel 472VU:

— ANN LT switch which is in READ

position from above.

— The fault light on the 

system annunciator com

4. On the overhead panel 430VU:

— Release (out) both the CTR TK PUMP

p/bsw.

— The OFF lights on the 

p/bsw come ON.

5. On the maintenance panel 472VU:

— Push in the MFA RESET switch. — The FAULT light on the 

system annunciator goe

6. On the panel 132VU:

— Remove the tags and close circuit

breakers 1QQ, 2QQ and 3QQ.

7. On the overhead panel 430VU:

— Push (in) both the the CTR TK PUMP

p/bsw.

— The OFF lights on the 

p/bsw go OFF.

8. On the maintenance panel 472VU:

— With the ANN LT switch still in the

READ position.

— The FAULT light on the 

system annunciator sta

36
DATE : Sep 09/94 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 22/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

— De-energize the aircraft electrical circuits 

24-41-00 Page block 301).

— Remove the tag and close these circuit breake

11. On the panel 132VU:

— Remove the tags and close circuit

breakers 1QQ.

12. On the maintenance panel 472VU:

— Push in the MFA RESET switch. — The FAULT light on the 

system annunciator goe

13. On the panel 132VU:

— Open, safety and tag circuit breaker

2QQ.

— R INR scavenge pump st

14. On the maintenance panel 472VU:

— With the ANN LT switch in the READ

position.

— The FAULT light on the 

system annunciator com

15. On the panel 132VU:

— Remove the tags and close circuit

breakers 2QQ.

16. On the maintenance panel 472VU:

— Push in the MFA RESET switch. — The FAULT light on the 

system annunciator goe

— Put the ANN LT switch in the OFF

position.

PANEL DESIGNATION FIN LOCA

101VU FUEL/L INNER TK PUMP2/SUPPLY 1QA ESS1

101VU FUEL/R INNER TK PUMP1/SUPPLY 2QA ESS1

101VU FUEL/L INNER TK PUMP1/SUPPLY 7QA GEN2

101VU FUEL/R INNER TK PUMP2/SUPPLY 8QA GEN2

101VU FUEL/CTR TK/L PUMP SUPPLY 99QA ESS/

101VU FUEL/CTR TK/L PUMP SUPPLY 100QA GEN2

37
DATE : Sep 09/94 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 22/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

F. DOCUMENTATION

Write in the applicable aircraft records that you have don

given in the Service Bulletin.

38
DATE : Sep 09/94 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 22/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 1 Sheet 1

Location

39
DATE : Sep 09/94 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 22/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 1 Sheet 2

Location

40
DATE : Sep 09/94 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 22/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 2 Sheet 1

Flow Chart (Config. 01 or 02 or 03)

41
DATE : Sep 09/94 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 22/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 2 Sheet 2

Flow Chart (Config. 01 or 02 or 03)

42
DATE : Sep 09/94 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 22/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 2 Sheet 3

Flow Chart (Config. 01 or 02 or 03)

43
DATE : Sep 09/94 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 22/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 2 Sheet 4

Flow Chart (Config. 01 or 02 or 03)

44
DATE : Sep 09/94 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 22/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 2 Sheet 5

Flow Chart (Config. 01 or 02 or 03)

45
DATE : Sep 09/94 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 22/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 2 Sheet 6

Flow Chart (Config. 01 or 02 or 03)

46
DATE : Sep 09/94 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 22/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 2 Sheet 7

Flow Chart (Config. 01 or 02 or 03)

47
DATE : Sep 09/94 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 22/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 2 Sheet 8

Flow Chart (Config. 01 or 02 or 03)

48
DATE : Sep 09/94 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 22/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 2 Sheet 9

Flow Chart (Config. 01 or 02 or 03)

49
DATE : Sep 09/94 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 22/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 3 Sheet 1

Flow Chart (Config. 04)

50
DATE : Sep 09/94 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 22/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 3 Sheet 2

Flow Chart (Config. 04)

51
DATE : Sep 09/94 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 22/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 3 Sheet 3

Flow Chart (Config. 04)

52
DATE : Sep 09/94 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 22/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 3 Sheet 4

Flow Chart (Config. 04)

53
DATE : Sep 09/94 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 22/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 3 Sheet 5

Flow Chart (Config. 04)

54
DATE : Sep 09/94 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 22/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 3 Sheet 6

Flow Chart (Config. 04)

55
DATE : Sep 09/94 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 22/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 3 Sheet 7

Flow Chart (Config. 04)

56
DATE : Sep 09/94 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 22/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 3 Sheet 8

Flow Chart (Config. 04)

57
DATE : Sep 09/94 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 22/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 3 Sheet 9

Flow Chart (Config. 04)

58
DATE : Sep 09/94 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 22/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 4 Sheet 1

Removal/Installation of Fairings under Wing Bottom Skin 

59
DATE : Sep 09/94 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 22/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 5 Sheet 1

Removal/Installation of LH Hydraulic Panel

60
DATE : Sep 09/94 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 22/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 5 Sheet 2

Removal/Installation of LH Hydraulic Panel

61
DATE : Sep 09/94 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 22/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 6 Sheet 1

Removal/Installation of RAT Adjustable Rod

62
DATE : Sep 09/94 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 22/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 7 Sheet 1

Removal/Installation of RAT Panel

63
DATE : Sep 09/94 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 22/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 7 Sheet 2

Removal/Installation of RAT Panel

64
DATE : Sep 09/94 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 22/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 8 Sheet 1

Repair of Holes

65
DATE : Sep 09/94 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 22/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 8 Sheet 2

Repair of Holes

66
DATE : Sep 09/94 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 22/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 9 Sheet 1

Replace fasteners, hole H

67
DATE : Sep 09/94 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 22/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 10 Sheet 1

Replace fasteners, hole I

68
DATE : Sep 09/94 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 22/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 11 Sheet 1

Replace fasteners, holes K,L,M and N.(Kit A06R04)

69
DATE : Sep 09/94 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 22/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 12 Sheet 1

Replace fasteners, holes U,V,W,X,Y (Kit A09 and A10

70
DATE : Sep 09/94 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 22/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 12 Sheet 2

Replace fasteners, holes U,V,W,X,Y (Kit A09 and A10

71
DATE : Sep 09/94 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 22/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 13 Sheet 1

Replace fasteners (Kit A07R02)

72
DATE : Sep 09/94 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 22/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 13 Sheet 2

Replace fasteners (Kit A07R02)

73
DATE : Sep 09/94 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 22/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 14 Sheet 1

Replace fasteners, holes K,L,M and N.(Kit A08R01)

74
DATE : Sep 09/94 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 22/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 15 Sheet 1

Fitting Cut-out Principle

75
DATE : Sep 09/94 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 22/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 15 Sheet 2

Fitting Cut-out Principle

76
DATE : Sep 09/94 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 22/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 15 Sheet 3

Fitting Cut-out Principle

77
5 DATE : Sep 09/94 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 22/06 Page : 1 of 

Printed in FRANCE © AIRBUS, 2006 All rights reserved
DATE : Sep 09/94 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 22/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 1 Sheet 1

Inspection Report

2
DATE : Sep 09/94 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 22/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 1 Sheet 2

Inspection Report

3
5 DATE : Sep 09/94 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 22/06 Page : 1 of 

Printed in FRANCE © AIRBUS, 2006 All rights reserved

A - SB WILL BE embodied............. YES/NO (if NO p

If YES, aircraft concerned (as per SB effectivity by default) and 

(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 th

information is needed prior to next normal revision or prior to S

please indicate required service:

Either: Modification Operational Impact (MOI), if available. . YE

Or : Intermediate revision. ................ YE

Important Information: This SB will only be incorporated in your m

operational documentation if this sheet is returned to Airbus and 

duly authorised representative. With the next feasible revision, 

result in

- updating of maintenance documentation to show pre and post S

- updating of maintenance and operational documentation to show 

after embodiment.

If this SB requires previous or simultaneous accomplishment of ot

Airbus shall automatically include them in the manual revisions. 

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.
5 DATE : Sep 09/94 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 22/06 Page : 1 of 

Printed in FRANCE © AIRBUS, 2006 All rights reserved

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

- Quality rating of this SB 

- Quality rating of the Accomplishment Instructions 

- Quality rating of the Illustrations 

- Is this SB easy to understand ? 

If you have had difficulties in the accomplishment of this SB plea

the area(s) and give a short description of the issue.

Planning Material Instruct

X Effectivity X Kit content X Preparat

X Reason X List of Materials X Mod/Insp

X Manpower Operator Supplied X Test

X References X Re-identification X Close-Up

X Publication X Tooling X Illustra

Comments :

Operator : Date:

Name/Title :

Please return this form to :

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC

Attn : SEM4 Service Bulletins Management

FAX : (33) 5 61 93 42 51

Or via your Resident Customer Support Office.