@A300

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

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

ATA SYSTEM: 53

TITLE: FUSELAGE - GENERAL - REINFORCE THE FLOOR CROSSBEAMS AT

FR22/FR23 AND FR61/FR62

MODIFICATION No.: 13434D23217

This page transmits Revision No.02 of Service Bulletin No.A300-53-0389

ADDITIONAL WORK

**CONF ALL

No additional work is required by this revision for aircraft modified by any previous issue.

REASON

Revision No. 02 issued to:

- correct AMM references

- add rework areas and figures

- incorporate minor changes.

CHANGES

SUMMARY

EFFECTIVITY OPERATOR LIST UPDATED R

CONCURRENT REQUIREMENTS CONCURRENT REQUIREMENTS UPDATED R

Fig. A-GSAAA FIGURE SOLUTION UPDATED R

Fig. A-GSAAA Sheet 02 SHEET ADDED N

Fig. A-GSB FIGURE DELETED FOR APPLICABLE MSN D

PLANNING INFORMATION

EFFECTIVITY EFFECTIVITY RELATED INFORMATION

UPDATED

R

CONCURRENT REQUIREMENTS CONCURRENT SB LIST UPDATED R

APPROVAL APPROVAL UPDATED R

WEIGHT AND BALANCE WEIGHT UPDATED

BALANCE UPDATED

R

WEIGHT UPDATED

BALANCE UPDATED

R

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

REVISION No.: 02 - Apr 27/11 Page: 1

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@A300

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

WEIGHT UPDATED

BALANCE UPDATED

R

REFERENCES REFERENCED DOCUMENTATION UPDATED R

REFERENCED DOCUMENTATION UPDATED R

REFERENCED DOCUMENTATION UPDATED R

MATERIAL INFORMATION

MATERIAL - PRICE AND AVAILABILITY

Price and Availability PRICE AND AVAILABILITY UPDATED

MATERIAL SET UPDATED

R

ACCOMPLISHMENT INSTRUCTIONS

TASK 530389- 831-848-001-

MODIFICATION

Subtask 530389-910-201-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

REFERENCES UPDATED

R

Subtask 530389-839-201-001 SUBTASK SOLUTION UPDATED R

Subtask 530389-910-201-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

REFERENCES UPDATED

R

Subtask 530389-839-201-001 SUBTASK SOLUTION UPDATED R

Subtask 530389-910-201-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

REFERENCES UPDATED

R

Subtask 530389-839-201-001 SUBTASK SOLUTION UPDATED R

Subtask 530389-941-201-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

REFERENCES UPDATED

R

Subtask 530389-941-201-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

REFERENCES UPDATED

R

Subtask 530389-941-201-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

REFERENCES UPDATED

R

Subtask 530389-831-203-001 SUBTASK SOLUTION UPDATED R

Subtask 530389-831-207-001 SUBTASK SOLUTION UPDATED R

Subtask 530389-831-203-002 SUBTASK SOLUTION UPDATED

CONFIGURATION UPDATED

FIGURE REFERENCE UPDATED

REFERENCED DOCUMENTATION UPDATED

R

Subtask 530389-831-207-001 SUBTASK SOLUTION UPDATED R

Subtask 530389-831-203-003 SUBTASK SOLUTION UPDATED R

Subtask 530389-831-207-001 SUBTASK SOLUTION UPDATED R

Subtask 530389-942-201-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

REFERENCES UPDATED

R

Subtask 530389-942-201-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

REFERENCES UPDATED

R

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

REVISION No.: 02 - Apr 27/11 Page: 2

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@A300

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

Subtask 530389-942-201-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

REFERENCES UPDATED

R

Fig. A-GBGAA FIGURE SOLUTION UPDATED R

Fig. A-GBGAA Sheet 02 SHEET UPDATED R

Fig. A-GBGAA Sheet 03 SHEET UPDATED R

Fig. A-GBGAA Sheet 05 SHEET UPDATED R

Fig. A-GBGAA Sheet 08 SHEET ADDED N

FILLING INSTRUCTIONS

This Service Bulletin has been generated electronically and is reissued as a complete document.

Replace the complete document.

Put this Revision Transmittal Sheet in front of the Service Bulletin.

HISTORY OF PREVIOUS REVISIONS

This Revision is issued to :

incorporate the result of the validation report from A300-600 aircraft MSN 0605.

REVISION SEQUENCE

ORIGINAL: Jan 15/10

REVISION No. : 01 - May 21/10

REVISION No. : 02 - Apr 27/11

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

REVISION No.: 02 - Apr 27/11 Page: 3

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@A300

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

This Page Intentionally Left Blank

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

REVISION No.: 02 - Apr 27/11 Page: 4

6

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@A300

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.

ATA SYSTEM: 53

TITLE: FUSELAGE - GENERAL - REINFORCE THE FLOOR CROSSBEAMS AT

FR22/FR23 AND FR61/FR62

**CONF ALL

MODIFICATIONS

MODIFICATION CLASSIFICATION

MAJOR None

MINOR 13434D23217

NOTE: As per EASA IR 21, a minor change is one that has no appreciable effect on the

mass, balance, structural strength, reliability, operational characteristics affecting the

airworthiness of the product. All other changes are major changes.

REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

Some operators have reported cracks in the crossbeam at the junction with the cargo door actuator

support beam. The damage was located on the outboard row of rivets on the crossbeam at FR23. The

laboratory analysis has revealed that the cracks initiated in the fastener hole are propagated vertically.

The design of the forward and aft cargo door attachment is similar, the crossbeams at FR22, FR23,

FR61 and FR62 should be reinforced to avoid crack initiation.

This Service Bulletin details the procedure to install the reinforcement fittings and to relocate the

brackets at the floor crossbeams at FR22, FR23, FR61 and FR62.

NOTE: It is not necessary to accomplish the Inspection Service Bulletin No. A300-53-0390

before doing this Service Bulletin. This Service Bulletin can be accomplished directly as

given in the accomplishment instruction.

NOTE: To reach the mod advantages, this Service Bulletin is to be accomplished, if:

- Service Bulletin No. A300-53-0320 has been previously accomplished,

- none repair has been performed in the affected areas in accordance with SRM, All

Operators Telex 53-07, Inspection Service Bulletin No. A300-53-0321 or Repair

Approval Sheet (RAS).

In case of existing repairs, the operators are requested to contact Airbus Repair Support

before accomplishment of this Service Bulletin, for further instructions.

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

REVISION No.: 02 - Apr 27/11 Page: 1

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@A300

SERVICE BULLETIN

SUMMARY

The accomplishment of this Service Bulletin will :

- contribute to avoid the development of cracks,

- cancel the inspection requirements in accordance with the Inspection Service Bulletin No.

A300-53-0390.

GENERAL EVALUATION

EVALUATION TABLE

COMPLIANCE RECOMMENDED (1) CANCELS INSPECTION SB YES

POTENTIAL AD NO A/C OPERATION AFFECTED NO

RELIABILITY AFFECTED NO PAX COMFORT AFFECTED NO

COST SAVING NO ETOPS AFFECTED NO

STRUCTURAL LIFE EXTN YES VENDOR SB INVOLVED NO

NOTE (1): Service Bulletin recommended to be accomplished to prevent significant operational

disruptions.

MATERIAL PRICE INFORMATION

**CONF 001

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Kit 530389D01R02 1 1,410.00 Reinforcement and attachment parts

Kit 530389D02R01 1 1,410.00 Reinforcement and attachment parts

TOTAL 2,820.00

Component COMPD01 1 See SB Clamp and attachment parts

Standard tool TOOLD01 2 See SB Support Struts - FWD and AFT Cargo

Compartment Doors

**CONF 002

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Kit 530389D01R02 1 1,410.00 Reinforcement and attachment parts

Kit 530389D03R01 1 953.00 Reinforcement and attachment parts

TOTAL 2,363.00

Component COMPD01 1 See SB Clamp and attachment parts

Standard tool TOOLD01 2 See SB Support Struts - FWD and AFT Cargo

Compartment Doors

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

REVISION No.: 02 - Apr 27/11 Page: 2

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@A300

SERVICE BULLETIN

SUMMARY

**CONF 003

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Kit 530389D01R02 1 1,410.00 Reinforcement and attachment parts

Kit 530389D04R02 1 1,020.00 Reinforcement and attachment parts

TOTAL 2,430.00

Component COMPD01 1 See SB Clamp and attachment parts

Standard tool TOOLD01 2 See SB Support Struts - FWD and AFT Cargo

Compartment Doors

EFFECTIVITY

**CONF ALL

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

50W 69X 72U ABR AFG C2A DHL F2I FLM IAW IRA IRM JLJ

KYE KZU MIX MNB MSR NTR P2A RUN SOP TNO TSY

The equivalent of this Service Bulletin has been validated on A300-600 aircraft MSN 0605.

CONCURRENT REQUIREMENTS

NOTE: Accomplishment of this Service Bulletin requires the prior or simultaneous

accomplishment of the following Service Bulletin(s) or the equivalent production

modification(s):

Service Bulletin No. A300-53-0321

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: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

REVISION No.: 02 - Apr 27/11 Page: 3

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@A300

SERVICE BULLETIN

SUMMARY

MANPOWER

**CONF 001

Task 530389-831-848-001: MODIFICATION

TOTAL MANHOURS 37.00

ELAPSED TIME (HOURS) 26.00

**CONF 002

Task 530389-831-848-001: MODIFICATION

TOTAL MANHOURS 37.00

ELAPSED TIME (HOURS) 26.00

**CONF 003

Task 530389-831-848-001: MODIFICATION

TOTAL MANHOURS 35.00

ELAPSED TIME (HOURS) 26.00

APPENDICES

**CONF ALL

None

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

REVISION No.: 02 - Apr 27/11 Page: 4

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@A300

SERVICE BULLETIN

SUMMARY

**CONF ALL

SEAT TRACK 5

SEAT TRACK 3

SEAT TRACK 2

SEAT TRACK 4

Z130

FR21 FR22 FR23 FR24

SEAT TRACK 6

AREAS TO BE MODIFIED

FWD

A

A_SB_530389_6_SAAA_01_02

A

Figure A-GSAAA - Sheet 01

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

REVISION No.: 02 - Apr 27/11 Page: 5

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@A300

SERVICE BULLETIN

SUMMARY

**CONF ALL

SEAT TRACK 5

SEAT TRACK 3

SEAT TRACK 2

SEAT TRACK 4

A

SEAT TRACK 6

FR60 FR61 FR62 FR63

Z150

AREAS TO BE MODIFIED

FWD

A

A_SB_530389_6_SAAA_02_00

Figure A-GSAAA - Sheet 02

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

REVISION No.: 02 - Apr 27/11 Page: 6

6

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

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

ATA SYSTEM: 53

TITLE: FUSELAGE - GENERAL - REINFORCE THE FLOOR CROSSBEAMS AT

FR22/FR23 AND FR61/FR62

MODIFICATION No.: 13434D23217

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

The equivalent of this Service Bulletin has been validated on A300-600 aircraft MSN 0605.

(1) Models

B2-1C B2-203 B2K-3C B4-103 B4-120 B4-203 B4-2C C4-203

F4-203

(2) Effectivity by MSN

0003 0019 0041 0045 0047 0053 0055 0075 0079-0080 0082-0085 0090 0094-0095

0100-0101 0105 0107 0116-0117 0123-0126 0128-0129 0133-0137 0139 0141

0147-0152 0154-0157 0160 0170 0173 0175-0176 0180 0183-0185 0187 0189-0190

0196 0199-0200 0203-0204 0208 0210-0212 0216 0218-0220 0226-0227 0234-0236

0239 0243-0244 0247 0249-0250 0255-0256 0259 0261 0265 0274 0277 0289 0292

0299 0302 0304

(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: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

REVISION No.: 02 - Apr 27/11 Page: 1

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@A300

SERVICE BULLETIN

OPERATOR MSN

50W 0003

69X 0095

72U 0079

ABR 0148 0152 0184 0189 0199 0208 0219 0220 0234 0236 0250 0259

0274 0289

AFG 0180 0190

C2A 0211

DHL 0084 0085 0141 0149 0249 0265

F2I 0083 0094 0128 0133 0135 0136 0137 0156 0170 0235 0243

FLM 0082

IAW 0239

IRA 0080 0139 0151 0173 0185 0187 0226 0256 0299 0302

IRM 0055 0090 0160 0175 0204 0244

JLJ 0176

KYE 0053 0100 0216

KZU 0041 0101 0117

MIX 0125 0134 0157 0196 0203 0218

MNB 0019 0047 0123 0212 0277 0292 0304

MSR 0200 0255

NTR 0124 0155 0261

P2A 0116 0150

RUN 0075 0105 0107 0147 0154 0183

SOP 0126

TNO 0045 0210 0227 0247

TSY 0129

(4) Configuration by MSN

MSN CONFIGURATION

0003 0019 0041 0045 0047 0053 0055 0075 0079 0080 0082

0084 0085 0090 0094 0095 0100 0101 0105 0107 0116 0117

0123 0124 0125 0126 0128 0129 0133 0134 0135 0136 0137

0139 0141 0147 0148 0149 0150 0151 0152 0154 0155 0156

001

0083 0212 0256 0277 0292 003

0157 0160 0170 0173 0175 0176 0180 0183 0184 0185 0187

0189 0190 0196 0199 0200 0203 0204 0208 0210 0211 0216

0218 0219 0220 0226 0227 0234 0235 0236 0239 0243 0244

0247 0249 0250 0255 0259 0261 0265 0274 0289 0299 0302

0304

002

(5) Configuration definition

**CONF 001

Config. 001 is valid for passenger aircraft on which Modification No. 02611D02031

(FUSELAGE STRUCTURE - IMPROVE THE FATIGUE LIFE OF LONGITUDINAL LAP

JOINTS OF OUTER SKIN) is not embodied.

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

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@A300

SERVICE BULLETIN

**CONF 002

Config. 002 is valid for passenger aircraft on which Modification No. 02611D02031

(FUSELAGE STRUCTURE - IMPROVE THE FATIGUE LIFE OF LONGITUDINAL LAP

JOINTS OF OUTER SKIN) is embodied.

**CONF 003

Config. 003 is valid for all the freighter aircraft given in the effectivity of this Service

Bulletin as a standard configuration.

(6) Material Effectivity

**CONF 001

MATERIAL QTY PER A/C SEE NOTES

Kit 530389D01R02 1

Kit 530389D02R01 1

Component COMPD01 1

Consumable CMLD01 As required

Standard tool TOOLD01 2

**CONF 002

MATERIAL QTY PER A/C SEE NOTES

Kit 530389D01R02 1

Kit 530389D03R01 1

Component COMPD01 1

Consumable CMLD01 As required

Standard tool TOOLD01 2

**CONF 003

MATERIAL QTY PER A/C SEE NOTES

Kit 530389D01R02 1

Kit 530389D04R02 1

Component COMPD01 1

Consumable CMLD01 As required

Standard tool TOOLD01 2

**CONF ALL

B. CONCURRENT REQUIREMENTS

NOTE: Accomplishment of this Service Bulletin requires the prior or simultaneous

accomplishment of the following Service Bulletin(s) or the equivalent

production modification(s):

Service Bulletin No. A300-53-0321

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

REVISION No.: 02 - Apr 27/11 Page: 3

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@A300

SERVICE BULLETIN

C. REASON

(1) History

Some operators have reported cracks in the crossbeam at the junction with the cargo

door actuator support beam. The damage was located on the outboard row of rivets on

the crossbeam at FR23. The laboratory analysis has revealed that the cracks initiated in

the fastener hole are propagated vertically. The design of the forward and aft cargo door

attachment is similar, the crossbeams at FR22, FR23, FR61 and FR62 should be

reinforced to avoid crack initiation.

(2) Objective/Action

This Service Bulletin details the procedure to install the reinforcement fittings and to

relocate the brackets at the floor crossbeams at FR22, FR23, FR61 and FR62.

NOTE: It is not necessary to accomplish the Inspection Service Bulletin No.

A300-53-0390 before doing this Service Bulletin. This Service Bulletin

can be accomplished directly as given in the accomplishment instruction.

NOTE: To reach the mod advantages, this Service Bulletin is to be

accomplished, if:

- Service Bulletin No. A300-53-0320 has been previously

accomplished,

- none repair has been performed in the affected areas in accordance

with SRM, All Operators Telex 53-07, Inspection Service Bulletin No.

A300-53-0321 or Repair Approval Sheet (RAS).

In case of existing repairs, the operators are requested to contact Airbus

Repair Support before accomplishment of this Service Bulletin, for further

instructions.

(3) Advantages

The accomplishment of this Service Bulletin will :

- contribute to avoid the development of cracks,

- cancel the inspection requirements in accordance with the Inspection Service

Bulletin No. A300-53-0390.

(4) Operational/Maintenance Consequences

None

D. DESCRIPTION

To accomplish this Service Bulletin it is necessary to :

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

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@A300

SERVICE BULLETIN

**CONF 001

Task 530389-831-848-001: MODIFICATION

(1) Remove the existing fasteners and brackets from the crossbeam at FR22 and FR23.

(2) Rotating Probe Inspection at the crossbeam FR22 and FR23.

(3) Install the reinforcement at the crossbeam at FR22 and FR23.

(4) Remove the existing fasteners from the crossbeam FR61 and FR62.

(5) Rotating Probe Inspection at the crossbeam FR61 and FR62.

(6) Install the reinforcement and brackets at the crossbeam at FR61 and FR62.

**CONF 002

Task 530389-831-848-001: MODIFICATION

(1) Remove the existing fasteners from the crossbeam at FR22 and FR23.

(2) Rotating Probe Inspection at the crossbeam at FR22 and FR23.

(3) Install the reinforcement at the crossbeam at FR22 and FR23.

(4) Remove the existing fasteners from the crossbeam FR61 and FR62.

(5) Rotating Probe Inspection at the crossbeam FR61 and FR62.

(6) Install the reinforcement and brackets at the crossbeam at FR61 and FR62.

**CONF 003

Task 530389-831-848-001: MODIFICATION

(1) Remove the existing fasteners and the brackets from the crossbeam at FR22 and

FR23.

(2) Rotating Probe Inspection at the crossbeam at FR22 and FR23.

(3) Install the reinforcement and the brackets at the crossbeam at FR22 and FR23.

(4) Remove the existing fasteners from the crossbeam FR61 and FR62.

(5) Rotating Probe Inspection at the crossbeam FR61 and FR62.

(6) Install the reinforcement and brackets at the crossbeam at FR61 and FR62.

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

REVISION No.: 02 - Apr 27/11 Page: 5

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@A300

SERVICE BULLETIN

**CONF ALL

E. COMPLIANCE

(1) Classification

RECOMMENDED: Service Bulletin recommended to be accomplished to prevent

significant operational disruptions.

(2) Accomplishment Timescale

Accomplishment of this Service Bulletin is recommended at the earliest opportunity

where manpower and facilities are available.

F. APPROVAL

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

Approval No. EASA.21J.031.

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

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

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

before incorporation of the Service Bulletin.

Aircraft that listed in this Service Bulletin and have been converted to freighter aircraft may

have a difference in the affected area. In this event, the operator should contact the relevant

Customer Service to obtain the necessary information about the future/planned Service

Bulletins for the converted aircraft.

G. MANPOWER

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

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

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

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

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

included.

**CONF 001

Task 530389-831-848-001: MODIFICATION

Get Access 4.00

On Aircraft

Remove the existing fasteners and brackets from the

crossbeam at FR22 and FR23.

4.00

Rotating Probe Inspection at the crossbeam FR22 and

FR23.

4.00

Install the reinforcement at the crossbeam at FR22 and

FR23.

8.00

Remove the existing fasteners from the crossbeam

FR61 and FR62.

3.00

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

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@A300

SERVICE BULLETIN

Task 530389-831-848-001: MODIFICATION

Rotating Probe Inspection at the crossbeam FR61 and

FR62.

4.00

Install the reinforcement and brackets at the

crossbeam at FR61 and FR62.

6.00

Tests 1.00

Close-Up 3.00

TOTAL MANHOURS 37.00

ELAPSED TIME (HOURS) 26.00

**CONF 002

Task 530389-831-848-001: MODIFICATION

Get Access 4.00

On Aircraft

Remove the existing fasteners from the crossbeam at

FR22 and FR23.

4.00

Rotating Probe Inspection at the crossbeam at FR22

and FR23.

4.00

Install the reinforcement at the crossbeam at FR22 and

FR23.

8.00

Remove the existing fasteners from the crossbeam

FR61 and FR62.

3.00

Rotating Probe Inspection at the crossbeam FR61 and

FR62.

4.00

Install the reinforcement and brackets at the

crossbeam at FR61 and FR62.

6.00

Tests 1.00

Close-Up 3.00

TOTAL MANHOURS 37.00

ELAPSED TIME (HOURS) 26.00

**CONF 003

Task 530389-831-848-001: MODIFICATION

Get Access 4.00

On Aircraft

Remove the existing fasteners and the brackets from

the crossbeam at FR22 and FR23.

4.00

Rotating Probe Inspection at the crossbeam at FR22

and FR23.

4.00

Install the reinforcement and the brackets at the

crossbeam at FR22 and FR23.

6.00

Remove the existing fasteners from the crossbeam

FR61 and FR62.

3.00

Rotating Probe Inspection at the crossbeam FR61 and

FR62.

4.00

Install the reinforcement and brackets at the

crossbeam at FR61 and FR62.

6.00

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

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@A300

SERVICE BULLETIN

Task 530389-831-848-001: MODIFICATION

Tests 1.00

Close-Up 3.00

TOTAL MANHOURS 35.00

ELAPSED TIME (HOURS) 26.00

**CONF ALL

H. WEIGHT AND BALANCE

**CONF 001

The weight and balance estimates given in this Service Bulletin are based on the

Manufacturer’s Empty Weight (MEW) and do not include operator item’s. For the definition of

MEW and operator’s items refer to Weight and Balance Manual (WBM) Chapter 1-00-07.

Manufacturers Empty Weight +0.642 KG (+1.4153 LB)

Effect on Balance +17.233 KGM (+124.646 LB.FT )

**CONF 002

The weight and balance estimates given in this Service Bulletin are based on the

Manufacturer’s Empty Weight (MEW) and do not include operator item’s. For the definition of

MEW and operator’s items refer to Weight and Balance Manual (WBM) Chapter 1-00-07.

Manufacturers Empty Weight +0.574 KG (+1.2654 LB)

Effect on Balance +16.172 KGM (+116.972 LB.FT )

**CONF 003

The weight and balance estimates given in this Service Bulletin are based on the

Manufacturer’s Empty Weight (MEW) and do not include operator item’s. For the definition of

MEW and operator’s items refer to Weight and Balance Manual (WBM) Chapter 1-00-07.

Manufacturers Empty Weight +0.520 KG (+1.1463 LB)

Effect on Balance +15.314 KGM (+110.766 LB.FT )

**CONF ALL

I. ELECTRICAL LOAD DATA

Not Changed

J. REFERENCES

**CONF 001

Aircraft Maintenance Manual (AMM) 06-21-53 24-00-00 24-41-00

25-51-00 25-51-11 25-52-11

52-30-00 52-31-11 52-33-11

52-33-18

All Operators Telex (AOT) 53-07

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

REVISION No.: 02 - Apr 27/11 Page: 8

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Consumable Material List (CML)

Elec. Std. Practices Manual (ESPM) 20-33-11 20-33-33 20-55-00

Non Destructive Test Manual (NTM) 51-30-10

Service Bulletin (SB) A300-53-0320

A300-53-0321

A300-53-0390

Standards Manual (SM)

Structural Repair Manual (SRM) 51-30-31 51-30-40 51-30-47

51-40-12 51-40-20

Weight and Balance Manual (WBM) Weight and Balance Manual

(WBM) Chapter 1-00-07

**CONF 002

Aircraft Maintenance Manual (AMM) 06-21-53 24-00-00 24-41-00

25-51-00 25-51-11 25-52-11

52-30-00 52-31-11 52-33-11

52-33-18

All Operators Telex (AOT) 53-07

Consumable Material List (CML)

Elec. Std. Practices Manual (ESPM) 20-33-11 20-33-33 20-55-00

Non Destructive Test Manual (NTM) 51-30-10

Service Bulletin (SB) A300-53-0320

A300-53-0321

A300-53-0390

Standards Manual (SM)

Structural Repair Manual (SRM) 51-27-11 51-30-31 51-30-40

51-30-47 51-40-12 51-40-20

Weight and Balance Manual (WBM) Weight and Balance Manual

(WBM) Chapter 1-00-07

**CONF 003

Aircraft Maintenance Manual (AMM) 06-21-53 24-00-00 24-41-00

25-51-00 25-51-11 25-52-11

52-30-00 52-31-11 52-33-11

52-33-18

All Operators Telex (AOT) 53-07

Consumable Material List (CML)

Elec. Std. Practices Manual (ESPM) 20-33-11 20-33-33 20-55-00

Non Destructive Test Manual (NTM) 51-30-10

Service Bulletin (SB) A300-53-0320

A300-53-0321

A300-53-0390

Standards Manual (SM)

Structural Repair Manual (SRM) 51-30-31 51-30-40 51-30-47

51-40-12 51-40-20 53-13-00

Weight and Balance Manual (WBM) Weight and Balance Manual

(WBM) Chapter 1-00-07

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**CONF ALL

K. PUBLICATION AFFECTED

**CONF 001

Structural Repair Manual (SRM) 53-13-00 53-17-00

**CONF 002

Structural Repair Manual (SRM) 53-13-00 53-17-00

**CONF 003

Structural Repair Manual (SRM) 53-13-00 53-17-00

**CONF ALL

L. INTERCHANGEABILITY/MIXABILITY

Not Applicable

M. SPARES

None

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

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2. MATERIAL INFORMATION

**CONF ALL

A. MATERIAL - PRICE AND AVAILABILITY

(1) Procurement Addresses

Kit 530389D01R02

Kit 530389D02R01

Kit 530389D03R01

Kit 530389D04R02

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:

AIRBUS Material, Logistics and Suppliers

Weg beim Jaeger 150

D-22335 Hamburg

Germany

For ordering by internet:

http://spares.airbus.com

For SB Kits by fax: +49 40 50 76 25 90

For Spares by fax : +49 40 50 76 40 12

Component COMPD01 Parts to be procured from:

B/E Aerospace Consumables Management

GmbH

Nordportbogen 6

D-22848 Norderstedt

Germany

Tel: +49 40 82 22 85 0

Fax: +49 40 82 22 85 31 00 5

(2) Price and Availability

Kit 530389D01R02

Cost 1,410.00 USD

Availability 120 calendar days from receipt of order

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

order. If you require Kits 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

at the issue date of the Service Bulletin.

Kit 530389D02R01

Cost 1,410.00 USD

Availability 120 calendar days from receipt of order

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

order. If you require Kits before this time, please include a retrofit planning schedule with

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

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The sales terms (costs and availability) are estimated in relation to economic conditions

at the issue date of the Service Bulletin.

Kit 530389D03R01

Cost 953.00 USD

Availability 120 calendar days from receipt of order

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

order. If you require Kits 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

at the issue date of the Service Bulletin.

Kit 530389D04R02

Cost 1,020.00 USD

Availability 120 calendar days from receipt of order

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

order. If you require Kits 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

at the issue date of the Service Bulletin.

B. INDUSTRY SUPPORT INFORMATION

AIRBUS will provide a 15% reduction to the applicable sales prices given in the paragraph

’Price and Availability’ for orders placed before 31st of December 2015.

C. LIST OF COMPONENTS

Kit 530389D01R02

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

NOTES

4 ASNA2528-3 35 NUT

5 ASNA2528-3A 15 NUT

6 EN6115K3-3 19 BOLT

10 EN6115K3X5 16 BOLT

12 EN6115K3AX5 4 BOLT

16 DAN11-6X 7 COLLAR

36 EN6081D4-07 2 RIVET

38 EN6081D6-09 4 RIVET

40 A5327429220000 1 PLATE

41 A5327429220600 1 PLATE

42 A5327415220600 1 ANGLE

43 A5327415220800 1 ANGLE

44 MS21051L3 1 NUT

45 ABS0337-01A 1 RECEPTCL

50 EN6069AD3-05 4 RIVET

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

NOTES

51 EN6115K3A5 10 BOLT

52 EN6115K3AX3 1 BOLT

53 EN6069D4-05 1 RIVET

55 DAN5-6-6X 7 PIN

56 DAN5-6-6Y 7 PIN

57 DAN11-6Y 7 COLLAR

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 530389D02R01

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

NOTES

1 A5378103421000 1 RNFRCMNT

2 A5378103421200 1 RNFRCMNT

3 A5378103421800 1 RNFRCMNT

4 ASNA2528-3 32 NUT

5 ASNA2528-3A 18 NUT

6 EN6115K3-3 10 BOLT

7 EN6115K3-4 4 BOLT

8 EN6115K3-5 2 BOLT

9 EN6115K3X4 2 BOLT

10 EN6115K3X5 14 BOLT

11 EN6115K3AX4 2 BOLT

12 EN6115K3AX5 4 BOLT

13 EN6115K3AX6 2 BOLT

14 EN6115K3A6 10 BOLT

15 DAN5-6-4X 2 PIN

16 DAN11-6X 9 COLLAR

55 DAN5-6-6X 7 PIN

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 530389D03R01

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

NOTES

4 ASNA2528-3 32 NUT

5 ASNA2528-3A 14 NUT

6 EN6115K3-3 16 BOLT

9 EN6115K3X4 2 BOLT

10 EN6115K3X5 14 BOLT

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

NOTES

12 EN6115K3AX5 2 BOLT

13 EN6115K3AX6 2 BOLT

14 EN6115K3A6 10 BOLT

16 DAN11-6X 7 COLLAR

20 A5378103420600 1 RNFRCMNT

21 A5378103422000 1 RNFRCMNT

55 DAN5-6-6X 7 PIN

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 530389D04R02

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

NOTES

4 ASNA2528-3 28 NUT

5 ASNA2528-3A 8 NUT

8 EN6115K3-5 2 BOLT

10 EN6115K3X5 6 BOLT

13 EN6115K3AX6 2 BOLT

16 DAN11-6X 7 COLLAR

22 A5378103423400 1 RNFRCMNT

23 MS21076L4N 2 NUT

25 A5377469720000 1 ANGLE

30 EN6115K3X6 10 BOLT

31 EN6115K3X7 10 BOLT

32 EN6115K3AX7 6 BOLT

35 EN6081D3-06 4 RIVET

36 EN6081D4-07 4 RIVET

37 EN6081D5-07 4 RIVET

38 EN6081D6-07 18 RIVET

55 DAN5-6-6X 7 PIN

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: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

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D. LIST OF MATERIALS - OPERATOR SUPPLIED

(1) Consumable Materials

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO CML

MAT. No.

QTY PER A/C SEE

NOTES

Corrosion Inhibiting Brush

Consistency

09-013 As required

Cleaning Solvent 11-016 As required

Solvent General Purpose 11-026 As required

Anti-Corrosion Primer

(polyurethane)

16-001 As required

Polyurethane Topcoat Grey (for

Internal Applic.)

16-002 As required

Wash Primer 16-020 As required

(2) Components

Component COMPD01

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

NOTES

70 NAS1801-3-26 1 SCREW

71 NAS1149D0332K 2 WASHER

72 NSA5527-03-01D 1 SPACER

73 NSA5527-03-08D 1 SPACER

74 MS21042-3 1 NUT

75 MS21919WCH3 1 CLAMP

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.

(3) Equipment

None

E. PARTS TO BE RE-IDENTIFIED BY OPERATOR

None

F. TOOLING

(1) Tooling - Price and Availability

None

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

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(2) Tools

Standard tool TOOLD01

ITEM TOOL N ̊ TOOL NAME QTY SEE

NOTES

98A52307523000 Support Struts - FWD and AFT

Cargo Compartment Doors

2 (1)

NOTE (1): The safety equipments are operator supplied.

(3) Special Tools

Fatigue Technology Incorporated (FTI) has allocated the following tool kit number for

cold working, refer to FTI Tooling List No. FTI-A300-53-0389-1.

NOTE: For the definition of capital, durable and expandable tools, refer to

SIL51-012.

- Capital Tool Kit No : FTI-FT20-LB20-CAP

. The capital tools provided in this kit are not specific to this Service Bulletin and

are normally already available in operator’s stock as a long term investment or

can be loaned from FTI.

- Durable Tool Kit No : DK-A300530389-1

. The capital tools provided in this kit are not specific to this Service Bulletin and

are normally already available in operator’s stock as a long term investment or

can be loaned from FTI.

- Expendable Tool Kit No : EK-A300530389-1

. The capital tools provided in this kit are not specific to this Service Bulletin and

are normally already available in operator’s stock as a long term investment or

can be loaned from FTI.

Operators interested in obtaining the FTI tool kit should contact:

Fatigue Technology Inc.

401 ANDOVER PARK EAST

SEATTLE, WA 98188-2868

USA

E-mail: sales@fatiguetech.com

E-mail: aog@fatiguetech.com

Phone: (1) 206 246 2010

Fax: (1) 206 244 9886

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3. ACCOMPLISHMENT INSTRUCTIONS

Task 530389-831-848-001 - MODIFICATION

WARNING: MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS

INCLUDED IN THE REFERENCED PROCEDURES

CAUTION: ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP ELECTRICAL

WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY AND

MECHANICALLY SERVICEABLE).

WHEN YOU DO MAINTENANCE WORK, REPAIRS OR MODIFICATIONS,

ALWAYS KEEP ELECTRICAL WIRING, COMPONENTS AND THE WORK AREA

AS CLEAN AS POSSIBLE. TO DO THIS :

- PUT PROTECTION, SUCH AS PLASTIC SHEETING, CLOTHS, ETC; AS

NECESSARY ON ELECTRICAL WIRING AND COMPONENTS

- REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND

OTHER CONTAMINATION.

THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION

AND DAMAGE TO THE ELECTRICAL WIRING INSTALLATION.

IF THERE IS CONTAMINATION REFER TO ESPM 20-55-00.

Task Associated Data

**CONF 001

Zone

130 150

Manpower

TOTAL MANHOURS 37.00

ELAPSED TIME (HOURS) 26.00

**CONF 002

Zone

130 150

Manpower

TOTAL MANHOURS 37.00

ELAPSED TIME (HOURS) 26.00

**CONF 003

Zone

130 150

Manpower

TOTAL MANHOURS 35.00

ELAPSED TIME (HOURS) 26.00

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

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**CONF ALL

A. GENERAL

**CONF 001

(1) Subtask 530389-910-201-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

Material necessary to do the job

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Corrosion Inhibiting Brush

Consistency

09-013 As required

Cleaning Solvent 11-016 As required

Anti-Corrosion Primer

(polyurethane)

16-001 As required

Polyurethane Topcoat Grey

(for Internal Applic.)

16-002 As required

Wash Primer 16-020 As required

References

Aircraft Maintenance Manual (AMM) 06-21-53, Page Block 001

Consumable Material List (CML)

Structural Repair Manual (SRM) 51-30-31

51-30-40

51-40-12

51-40-20

(a) If 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.

(b) For the specification of materials (Mat. No.) given in this Service Bulletin (Refer to

the Consumable Materials List (CML)).

(c) For the location of access panels (Refer to AMM 06-21-53, Page Block 001).

(d) Remove the old sealant with non-metallic scrapers and a stiff brush.

(e) Drill and deburr the rivet holes (Refer to SRM 51-30-40).

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(f) After drilling and cutting, apply

Anti-Corrosion

Primer

(polyurethane)

16-001 As required

and

Polyurethane

Topcoat Grey (for

Internal Applic.)

16-002 As required

and

Wash Primer 16-020 As required

and (Refer to SRM 51-40-12) on the affected areas.

(g) Clean the reworked surfaces and the surfaces to be sealed with :

Cleaning Solvent 11-016 As required

(h) Apply

Corrosion Inhibiting

Brush Consistency

09-013 As required

on all mating surfaces.

(i) Install rivets and pins on all mating surfaces with :

Corrosion Inhibiting

Brush Consistency

09-013 As required

(j) For alternative and substitute fasteners (Refer to SRM 51-30-31).

(k) For the procedure to use sealant (Refer to SRM 51-40-20).

(l) Apply a sealant bead with :

Corrosion Inhibiting

Brush Consistency

09-013 As required

(m) Install only Hi-Lok fasteners with the interference fit in cold expanded holes.

(2) Subtask 530389-839-201-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

Write in the applicable aircraft records that you have done all the work given in this

Service Bulletin.

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**CONF 002

(1) Subtask 530389-910-201-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

Material necessary to do the job

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Corrosion Inhibiting Brush

Consistency

09-013 As required

Cleaning Solvent 11-016 As required

Anti-Corrosion Primer

(polyurethane)

16-001 As required

Polyurethane Topcoat Grey

(for Internal Applic.)

16-002 As required

Wash Primer 16-020 As required

References

Aircraft Maintenance Manual (AMM) 06-21-53, Page Block 001

Consumable Material List (CML)

Structural Repair Manual (SRM) 51-30-31

51-30-40

51-40-12

51-40-20

(a) If 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.

(b) For the specification of materials (Mat. No.) given in this Service Bulletin (Refer to

the Consumable Materials List (CML)).

(c) For the location of access panels (Refer to AMM 06-21-53, Page Block 001).

(d) Remove the old sealant with non-metallic scrapers and a stiff brush.

(e) Drill and deburr the rivet holes (Refer to SRM 51-30-40).

(f) After drilling and cutting, apply

Anti-Corrosion

Primer

(polyurethane)

16-001 As required

and

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Polyurethane

Topcoat Grey (for

Internal Applic.)

16-002 As required

and

Wash Primer 16-020 As required

and (Refer to SRM 51-40-12) on the affected areas.

(g) Clean the reworked surfaces and the surfaces to be sealed with :

Cleaning Solvent 11-016 As required

(h) Apply

Corrosion Inhibiting

Brush Consistency

09-013 As required

on all mating surfaces.

(i) Install rivets and pins on all mating surfaces with :

Corrosion Inhibiting

Brush Consistency

09-013 As required

(j) For alternative and substitute fasteners (Refer to SRM 51-30-31).

(k) For the procedure to use sealant (Refer to SRM 51-40-20).

(l) Apply a sealant bead with :

Corrosion Inhibiting

Brush Consistency

09-013 As required

(m) Install only Hi-Lok fasteners with the interference fit in cold expanded holes.

(2) Subtask 530389-839-201-001 - 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 530389-910-201-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

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Material necessary to do the job

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Corrosion Inhibiting Brush

Consistency

09-013 As required

Cleaning Solvent 11-016 As required

Anti-Corrosion Primer

(polyurethane)

16-001 As required

Polyurethane Topcoat Grey

(for Internal Applic.)

16-002 As required

Wash Primer 16-020 As required

References

Aircraft Maintenance Manual (AMM) 06-21-53, Page Block 001

Consumable Material List (CML)

Structural Repair Manual (SRM) 51-30-31

51-30-40

51-40-12

51-40-20

(a) If 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.

(b) For the specification of materials (Mat. No.) given in this Service Bulletin (Refer to

the Consumable Materials List (CML)).

(c) For the location of access panels (Refer to AMM 06-21-53, Page Block 001).

(d) Remove the old sealant with non-metallic scrapers and a stiff brush.

(e) Drill and deburr the rivet holes (Refer to SRM 51-30-40).

(f) After drilling and cutting, apply

Anti-Corrosion

Primer

(polyurethane)

16-001 As required

and

Polyurethane

Topcoat Grey (for

Internal Applic.)

16-002 As required

and

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Wash Primer 16-020 As required

and (Refer to SRM 51-40-12) on the affected areas.

(g) Clean the reworked surfaces and the surfaces to be sealed with :

Cleaning Solvent 11-016 As required

(h) Apply

Corrosion Inhibiting

Brush Consistency

09-013 As required

on all mating surfaces.

(i) Install rivets and pins on all mating surfaces with :

Corrosion Inhibiting

Brush Consistency

09-013 As required

(j) For alternative and substitute fasteners (Refer to SRM 51-30-31).

(k) For the procedure to use sealant (Refer to SRM 51-40-20).

(l) Apply a sealant bead with :

Corrosion Inhibiting

Brush Consistency

09-013 As required

(m) Install only Hi-Lok fasteners with the interference fit in cold expanded holes.

(2) Subtask 530389-839-201-001 - 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 ALL

B. PREPARATION

**CONF 001

(1) Subtask 530389-941-201-001 - Preparation

Manpower Resources

Skills NON SPECIFIC

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

REVISION No.: 02 - Apr 27/11 Page: 23

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Material necessary to do the job

Standard tool TOOLD01

ITEM TOOL N ̊ TOOL NAME QTY SEE

NOTES

98A52307523000 Support Struts - FWD and

AFT Cargo Compartment

Doors

2 (1)

NOTE (1): The safety equipments are operator supplied.

References

Aircraft Maintenance Manual (AMM) 06-21-53, Page Block 001

24-00-00, Page Block 301

24-41-00, Page Block 301

25-51-00, Page Block 401

25-51-11, Page Block 401

25-52-11, Page Block 401

52-30-00, Page Block 301

52-33-18, Page Block 401

52-33-18, Page Block 401

(a) Make sure that the aircraft is electrically grounded (Refer to AMM 24-00-00, Page

Block 301).

(b) Put access platform(s) in position

(c) De-energize the aircraft electrical circuits (Refer to AMM 24-41-00, Page Block

301).

(d) Open the FWD cargo-compartment door 811 (Refer to AMM 52-30-00, Page Block

301).

(e) Open the AFT cargo-compartment door 812 (Refer to AMM 52-30-00, Page Block

301).

(f) Disconnect the door actuator from the FWD and AFT cargo-compartment doors and

install :

98A52307523000 Support Struts -

FWD and AFT

Cargo

Compartment Doors

2

Refer to AMM 52-30-00, Page Block 301.

NOTE: Do not use the actuator safety lock(s).

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

REVISION No.: 02 - Apr 27/11 Page: 24

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(g) Open, safety and tag these circuit breaker(s) :

PANEL DESIGNATION FIN LOCATION SEE

NOTES

128VU HYDRAULIC/ACCU PRESS

CTL AND CARGO PUMP

7GX 803/C11

101VU ELEC HYD PUMP 23GX ALT2

NOTE: The location of the circuit breaker(s) can be different from the

location given in the table.

(h) Remove and retain the FWD cargo-compartment ceiling panels as necessary

(Refer to AMM 25-51-11, Page Block 401 and AMM 06-21-53, Page Block 001).

(i) Remove the door actuator lining between FR22 and FR23.

(j) Remove the FWD cargo-compartment actuator from the actuator support beam

(Refer to AMM 52-33-18, Page Block 401).

(k) Remove and retain the AFT cargo-compartment ceiling panels as necessary (Refer

to AMM 25-52-11, Page Block 401 and AMM 06-21-53, Page Block 001).

(l) Remove the door actuator lining between FR61 and FR62.

(m) Remove the AFT cargo-compartment actuator from the actuator support beam

(Refer to AMM 52-33-18, Page Block 401).

**CONF 002

(1) Subtask 530389-941-201-001 - Preparation

Manpower Resources

Skills NON SPECIFIC

Material necessary to do the job

Standard tool TOOLD01

ITEM TOOL N ̊ TOOL NAME QTY SEE

NOTES

98A52307523000 Support Struts - FWD and

AFT Cargo Compartment

Doors

2 (1)

NOTE (1): The safety equipments are operator supplied.

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

REVISION No.: 02 - Apr 27/11 Page: 25

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References

Aircraft Maintenance Manual (AMM) 06-21-53, Page Block 001

24-00-00, Page Block 301

24-41-00, Page Block 301

25-51-00, Page Block 401

25-51-11, Page Block 401

25-52-11, Page Block 401

52-30-00, Page Block 301

52-33-18, Page Block 401

52-33-18, Page Block 401

(a) Make sure that the aircraft is electrically grounded (Refer to AMM 24-00-00, Page

Block 301).

(b) Put access platform(s) in position

(c) De-energize the aircraft electrical circuits (Refer to AMM 24-41-00, Page Block

301).

(d) Open the FWD cargo-compartment door 811 (Refer to AMM 52-30-00, Page Block

301).

(e) Open the AFT cargo-compartment door 812 (Refer to AMM 52-30-00, Page Block

301).

(f) Disconnect the door actuator from the FWD and AFT cargo-compartment doors and

install :

98A52307523000 Support Struts -

FWD and AFT

Cargo

Compartment Doors

2

Refer to AMM 52-30-00, Page Block 301.

NOTE: Do not use the actuator safety lock(s).

(g) Open, safety and tag these circuit breaker(s) :

PANEL DESIGNATION FIN LOCATION SEE

NOTES

128VU HYDRAULIC/ACCU PRESS

CTL AND CARGO PUMP

7GX 803/C11

101VU ELEC HYD PUMP 23GX ALT2

NOTE: The location of the circuit breaker(s) can be different from the

location given in the table.

(h) Remove and retain the FWD cargo-compartment ceiling panels as necessary

(Refer to AMM 25-51-11, Page Block 401 and AMM 06-21-53, Page Block 001).

(i) Remove the door actuator lining between FR22 and FR23.

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

REVISION No.: 02 - Apr 27/11 Page: 26

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(j) Remove the FWD cargo-compartment actuator from the actuator support beam

(Refer to AMM 52-33-18, Page Block 401).

(k) Remove and retain the AFT cargo-compartment ceiling panels as necessary (Refer

to AMM 25-52-11, Page Block 401 and AMM 06-21-53, Page Block 001).

(l) Remove the door actuator lining between FR61 and FR62.

(m) Remove the AFT cargo-compartment actuator from the actuator support beam

(Refer to AMM 52-33-18, Page Block 401).

**CONF 003

(1) Subtask 530389-941-201-001 - Preparation

Manpower Resources

Skills NON SPECIFIC

Material necessary to do the job

Standard tool TOOLD01

ITEM TOOL N ̊ TOOL NAME QTY SEE

NOTES

98A52307523000 Support Struts - FWD and

AFT Cargo Compartment

Doors

2 (1)

NOTE (1): The safety equipments are operator supplied.

References

Aircraft Maintenance Manual (AMM) 06-21-53, Page Block 001

24-00-00, Page Block 301

24-41-00, Page Block 301

25-51-00, Page Block 401

25-51-11, Page Block 401

25-52-11, Page Block 401

52-30-00, Page Block 301

52-33-18, Page Block 401

52-33-18, Page Block 401

(a) Make sure that the aircraft is electrically grounded (Refer to AMM 24-00-00, Page

Block 301).

(b) Put access platform(s) in position

(c) De-energize the aircraft electrical circuits (Refer to AMM 24-41-00, Page Block

301).

(d) Open the FWD cargo-compartment door 811 (Refer to AMM 52-30-00, Page Block

301).

(e) Open the AFT cargo-compartment door 812 (Refer to AMM 52-30-00, Page Block

301).

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

REVISION No.: 02 - Apr 27/11 Page: 27

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SERVICE BULLETIN

(f) Disconnect the door actuator from the FWD and AFT cargo-compartment doors and

install :

98A52307523000 Support Struts -

FWD and AFT

Cargo

Compartment Doors

2

Refer to AMM 52-30-00, Page Block 301.

NOTE: Do not use the actuator safety lock(s).

(g) Open, safety and tag these circuit breaker(s) :

PANEL DESIGNATION FIN LOCATION SEE

NOTES

128VU HYDRAULIC/ACCU PRESS

CTL AND CARGO PUMP

7GX 803/C11

101VU ELEC HYD PUMP 23GX ALT2

NOTE: The location of the circuit breaker(s) can be different from the

location given in the table.

(h) Remove and retain the FWD cargo-compartment ceiling panels as necessary

(Refer to AMM 25-51-11, Page Block 401 and AMM 06-21-53, Page Block 001).

(i) Remove the door actuator lining between FR22 and FR23.

(j) Remove the FWD cargo-compartment actuator from the actuator support beam

(Refer to AMM 52-33-18, Page Block 401).

(k) Remove and retain the AFT cargo-compartment ceiling panels as necessary (Refer

to AMM 25-52-11, Page Block 401 and AMM 06-21-53, Page Block 001).

(l) Remove the door actuator lining between FR61 and FR62.

(m) Remove the AFT cargo-compartment actuator from the actuator support beam

(Refer to AMM 52-33-18, Page Block 401).

**CONF ALL

C. PROCEDURE

NOTE: It is not necessary to accomplish the Inspection Service Bulletin No.

A300-53-0390 before doing this Service Bulletin. This Service Bulletin can be

accomplished directly as given in the accomplishment instruction.

NOTE: To reach the mod advantages, this Service Bulletin is to be accomplished, if:

- Service Bulletin No. A300-53-0320 has been previously accomplished,

- none repair has been performed in the affected areas in accordance

with SRM, All Operators Telex 53-07, Inspection Service Bulletin No.

A300-53-0321 or Repair Approval Sheet (RAS).

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

REVISION No.: 02 - Apr 27/11 Page: 28

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SERVICE BULLETIN

In case of existing repairs, the operators are requested to contact Airbus

Repair Support before accomplishment of this Service Bulletin, for further

instructions.

**CONF 001

(1) Subtask 530389-831-201-001 - Remove the existing fasteners and brackets from

the crossbeam at FR22 and FR23.

Work Zones and Access Panels

Zone Access/Work location

130

Manpower Resources

Manhours 4.00

Minimum number of person 2

Subtask elapsed time 2.00

Skills AIRFRAME

Material necessary to do the job

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Solvent General Purpose 11-026 As required

References

Consumable Material List (CML)

Fig. A-GBAAA

Removal of the Existing Fasteners from

the Crossbeam at FR22 and FR23

Sheet 01

Sheet 02

Sheet 03

Sheet 04

WARNING: BEFORE YOU REMOVE ANY RIVETS FROM THE CROSSBEAM FR22

OR FR23, ENSURE THAT THE FORWARD DOOR ACTUATOR IS

DISCONNECTED FROM THE ACTUATOR BEAM.

(a) Remove the existing fasteners and brackets from the crossbeam at FR22.

1 Remove the fasteners and the bracket :

Refer to Fig. A-GBAAA Sheet 02, Detail B, and Fig. A-GBAAA Sheet 03,

Detail D

1 Bracket A5377420420000 Item (17) Discard

2 Clean the fasteners holes and the adjacent area with :

Solvent General

Purpose

11-026 As required

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

REVISION No.: 02 - Apr 27/11 Page: 29

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(b) If pins are installed in the actuator beam at FR22, remove them.

1 Remove the existing pins :

Refer to Fig. A-GBAAA Sheet 02, Detail B, and Fig. A-GBAAA Sheet 04,

Detail F

2 Clean the pin holes and the adjacent area with :

Solvent General

Purpose

11-026 As required

(c) Remove the fasteners from the crossbeam at FR23.

1 Remove the fasteners :

Refer to Fig. A-GBAAA Sheet 02, Detail C, and Fig. A-GBAAA Sheet 03,

Detail E

2 Clean the fastener holes and the adjacent area with :

Solvent General

Purpose

11-026 As required

(2) Subtask 530389-832-201-001 - Rotating Probe Inspection at the crossbeam FR22

and FR23.

Work Zones and Access Panels

Zone Access/Work location

130

Manpower Resources

Manhours 4.00

Minimum number of person 1

Subtask elapsed time 4.00

Skills AIRFRAME

References

Non Destructive Test Manual (NTM) 51-30-10 PART 1

Fig. A-GBCAA

Installation of the Reinforcement at the

Crossbeam at FR22 and FR23

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

(a) Rotating Probe Inspection at the crossbeam at FR22.

1 Do a rotating probe inspection of the fastener holes at FR22 (Refer to NTM

51-30-10 PART 1).

Refer to Fig. A-GBCAA Sheet 03, Detail D

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

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a If no crack(s) are found :

<1> - Refer to para. (3)(a).

b If crack(s) are found :

<1> Contact AIRBUS for further instructions.

(b) Rotating Probe Inspection at the crossbeam FR23.

1 Do a rotating probe inspection of the fastener holes at FR23 (Refer to NTM

51-30-10 PART 1).

Refer to Fig. A-GBCAA Sheet 04, Detail F

a If no crack(s) are found :

<1> - Refer to para. (3)(c).

b If crack(s) are found :

<1> Contact AIRBUS for further instructions.

(3) Subtask 530389-831-203-001 - Install the reinforcement at the crossbeam at FR22

and FR23.

Work Zones and Access Panels

Zone Access/Work location

130

Manpower Resources

Manhours 8.00

Minimum number of person 2

Subtask elapsed time 4.00

Skills AIRFRAME

Material necessary to do the job

Kit 530389D02R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 A5378103421000 1 RNFRCMNT

2 A5378103421200 1 RNFRCMNT

3 A5378103421800 1 RNFRCMNT

4 ASNA2528-3 32 NUT

5 ASNA2528-3A 18 NUT

6 EN6115K3-3 10 BOLT

7 EN6115K3-4 4 BOLT

8 EN6115K3-5 2 BOLT

9 EN6115K3X4 2 BOLT

10 EN6115K3X5 14 BOLT

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

REVISION No.: 02 - Apr 27/11 Page: 31

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SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

11 EN6115K3AX4 2 BOLT

12 EN6115K3AX5 4 BOLT

13 EN6115K3AX6 2 BOLT

14 EN6115K3A6 10 BOLT

15 DAN5-6-4X 2 PIN

16 DAN11-6X 9 COLLAR

55 DAN5-6-6X 7 PIN

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Solvent General Purpose 11-026 As required

References

Consumable Material List (CML)

Elec. Std. Practices Manual (ESPM) 20-33-11

20-33-33

Structural Repair Manual (SRM) 51-30-47

51-40-20

Fig. A-GBCAA

Installation of the Reinforcement at the

Crossbeam at FR22 and FR23

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

(a) Install the reinforcement at the crossbeam at FR22.

Refer to Fig. A-GBCAA Sheet 02, Detail B, Fig. A-GBCAA Sheet 03, Detail E, and

Fig. A-GBCAA Sheet 05

1 At FR22 install temporarily :

Refer to Fig. A-GBCAA Sheet 02, Detail B, Fig. A-GBCAA Sheet 03, Detail E

1 Reinforcement A5378103421000 Item 1

1 Reinforcement A5378103421200 Item 2

2 If no ’cold expansion’ drill the fastener holes and open to final dimension.

3 If ’cold expansion’ transfer drill the fastener holes and open to the specific

starting hole diameter.

4 Cold expand the specified fastener holes on the reinforcement and structure

where no cracks were found.

Refer to SRM 51-30-47

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

REVISION No.: 02 - Apr 27/11 Page: 32

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Refer to FTI Tooling List No. FTI-A300-53-0389-1

Refer to Fig. A-GBCAA Sheet 03, Detail E, and Fig. A-GBCAA Sheet 05

5 Ream the specified fastener holes on the reinforcement and structure with the

correct gage finish reamer.

Refer to Fig. A-GBCAA Sheet 03, Detail E, and Fig. A-GBCAA Sheet 05

6 Remove the temporarily installed Item 1 and Item 2.

7 Clean the fastener holes with :

Solvent General

Purpose

11-026 As required

8 Install the reinforcement, Item 1, and reinforcement, Item 2, with :

Refer to Fig. A-GBCAA Sheet 03, Detail E, and Fig. A-GBCAA Sheet 05

Refer to SRM 51-40-20

22 Nut ASNA2528-3 Item 4

4 Nut ASNA2528-3A Item 5

4 Bolt EN6115K3-4 Item 7

2 Bolt EN6115K3-5 Item 8

2 Bolt EN6115K3X4 Item 9

14 Bolt EN6115K3X5 Item 10

4 Bolt EN6115K3AX5 Item 12

2 Pin DAN5-6-4X Item 15

2 Collar DAN11-6X Item 16

(b) If nominal size pins have been removed from the actuator beam at FR22, install

new 1st oversize pins.

Refer to Fig. A-GBCAA Sheet 02, Detail B, Fig. A-GBCAA Sheet 05 and Fig. AGBCAA Sheet 06, Detail H

1 Install :

7 Pin DAN5-6-6X Item 55

7 Collar DAN11-6X Item 16

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

REVISION No.: 02 - Apr 27/11 Page: 33

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(c) Install the reinforcement at the crossbeam at FR23.

Refer to Fig. A-GBCAA Sheet 04, Detail G, and Fig. A-GBCAA Sheet 05

1 At FR23 install temporarily :

1 Reinforcement A5378103421800 Item 3

2 If no ’cold expansion’ drill the fastener holes and open to final dimension.

3 If ’cold expansion’ transfer drill the fastener holes and open to the specific

starting hole diameter.

4 Cold expand the specified fastener holes on the reinforcement and structure

where no cracks were found.

Refer to SRM 51-30-47

Refer to FTI Tooling List No. FTI-A300-53-0389-1

Refer to Fig. A-GBCAA Sheet 04, Detail G, and Fig. A-GBCAA Sheet 05

5 Ream the specified fastener holes on the reinforcement and structure with the

correct gage finish reamer.

Refer to Fig. A-GBCAA Sheet 04, Detail G, and Fig. A-GBCAA Sheet 05

6 Remove the temporarily installed Item 3.

7 Clean the fastener holes with :

Solvent General

Purpose

11-026 As required

8 Install the reinforcement, Item 3, with :

Refer to Fig. A-GBCAA Sheet 02, Detail C, Fig. A-GBCAA Sheet 04, Detail G,

and Fig. A-GBCAA Sheet 05

Refer to SRM 51-40-20

10 Nut ASNA2528-3 Item 4

14 Nut ASNA2528-3A Item 5

10 Bolt EN6115K3-3 Item 6

2 Bolt EN6115K3AX4 Item 11

2 Bolt EN6115K3AX6 Item 13

10 Bolt EN6115K3A6 Item 14

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(d) Perform minor amendment of screws, spacers and split conduits (Refer to ESPM

20-33-11 and ESPM 20-33-33).

(4) Subtask 530389-831-205-001 - Remove the existing fasteners from the crossbeam

FR61 and FR62.

Work Zones and Access Panels

Zone Access/Work location

150

Manpower Resources

Manhours 3.00

Minimum number of person 2

Subtask elapsed time 1.50

Skills AIRFRAME

Material necessary to do the job

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Solvent General Purpose 11-026 As required

References

Consumable Material List (CML)

Fig. A-GBNAA

Removal of the Existing Rivets from the

Crossbeam at FR61 and FR62

Sheet 01

Sheet 02

Sheet 03

Sheet 04

WARNING: BEFORE YOU REMOVE ANY RIVETS FROM THE CROSSBEAM

FR61 OR FR62, ENSURE THAT THE AFTER DOOR ACTUATOR IS

DISCONNECTED FROM THE ACTUATOR BEAM.

(a) Remove the existing fasteners from the crossbeam FR61.

1 Remove the existing fasteners :

Refer to Fig. A-GBNAA Sheet 02, Detail B, and Fig. A-GBNAA Sheet 03,

Detail D

2 Clean the fasteners holes and the adjacent area with :

Solvent General

Purpose

11-026 As required

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

REVISION No.: 02 - Apr 27/11 Page: 35

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(b) If pins are installed in the actuator beam at FR61, remove them.

1 Remove the existing pins :

Refer to Fig. A-GBNAA Sheet 02, Detail B, and Fig. A-GBNAA Sheet 04,

Detail F

2 Clean the pin holes and the adjacent area with :

Solvent General

Purpose

11-026 As required

(c) Remove the existing fasteners from the crossbeam FR62.

1 Remove the bracket, the receptacle and the fasteners :

Refer to Fig. A-GBNAA Sheet 02, Detail C, and Fig. A-GBNAA Sheet 03,

Detail E

1 Bracket A2557309120600 Item (43) Discard

1 Nut NAS1068C3 Item (44) Discard

1 Receptacle DAN367-01 Item (45) Discard

2 Clean the fastener holes and the adjacent area with :

Solvent General

Purpose

11-026 As required

(5) Subtask 530389-831-206-001 - Rotating Probe Inspection at the crossbeam FR61

and FR62.

Work Zones and Access Panels

Zone Access/Work location

150

Manpower Resources

Manhours 4.00

Minimum number of person 1

Subtask elapsed time 4.00

Skills AIRFRAME

References

Consumable Material List (CML)

Non Destructive Test Manual (NTM) 51-30-10 PART 1

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

REVISION No.: 02 - Apr 27/11 Page: 36

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References

Fig. A-GBPAA

Installation of the Reinforcement at the

Crossbeam at FR61 and FR62

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

(a) Rotating Probe Inspection at the crossbeam at FR61.

1 Do a rotating probe inspection of the fastener holes at FR61 (Refer to NTM

51-30-10 PART 1).

Refer to Fig. A-GBPAA Sheet 03, Detail D

a If no crack(s) are found :

<1> - Refer to para. (6)(a).

b If crack(s) are found :

<1> Contact AIRBUS for further instructions.

(b) Rotating Probe Inspection at the crossbeam at FR62.

1 Do a rotating probe inspection of the fastener holes at FR62 (Refer to NTM

51-30-10 PART 1).

Refer to Fig. A-GBPAA Sheet 04, Detail F

a If no crack(s) are found :

<1> - Refer to para. (6)(c).

b If crack(s) are found :

<1> Contact AIRBUS for further instructions.

(6) Subtask 530389-831-207-001 - Install the reinforcement and brackets at the

crossbeam at FR61 and FR62.

Work Zones and Access Panels

Zone Access/Work location

150

Manpower Resources

Manhours 6.00

Minimum number of person 2

Subtask elapsed time 3.00

Skills AIRFRAME

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

REVISION No.: 02 - Apr 27/11 Page: 37

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@A300

SERVICE BULLETIN

Material necessary to do the job

Kit 530389D01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

4 ASNA2528-3 35 NUT

5 ASNA2528-3A 15 NUT

6 EN6115K3-3 19 BOLT

10 EN6115K3X5 16 BOLT

12 EN6115K3AX5 4 BOLT

16 DAN11-6X 7 COLLAR

36 EN6081D4-07 2 RIVET

38 EN6081D6-09 4 RIVET

40 A5327429220000 1 PLATE

41 A5327429220600 1 PLATE

42 A5327415220600 1 ANGLE

43 A5327415220800 1 ANGLE

44 MS21051L3 1 NUT

45 ABS0337-01A 1 RECEPTCL

50 EN6069AD3-05 4 RIVET

51 EN6115K3A5 10 BOLT

52 EN6115K3AX3 1 BOLT

53 EN6069D4-05 1 RIVET

55 DAN5-6-6X 7 PIN

56 DAN5-6-6Y 7 PIN

57 DAN11-6Y 7 COLLAR

Component COMPD01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

70 NAS1801-3-26 1 SCREW

71 NAS1149D0332K 2 WASHER

72 NSA5527-03-01D 1 SPACER

73 NSA5527-03-08D 1 SPACER

74 MS21042-3 1 NUT

75 MS21919WCH3 1 CLAMP

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Solvent General Purpose 11-026 As required

References

Consumable Material List (CML)

Elec. Std. Practices Manual (ESPM) 20-33-11

20-33-33

Structural Repair Manual (SRM) 51-30-47

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

REVISION No.: 02 - Apr 27/11 Page: 38

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@A300

SERVICE BULLETIN

References

Fig. A-GBPAA

Installation of the Reinforcement at the

Crossbeam at FR61 and FR62

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

(a) Install the reinforcement at the crossbeam at FR61.

Refer to Fig. A-GBPAA Sheet 02, Detail B, Fig. A-GBPAA Sheet 03, Detail E, and

Fig. A-GBPAA Sheet 05

1 At FR61 install temporarily :

1 Reinforcement A5327429220000 Item 40

2 If no ’cold expansion’ drill the fastener holes and open to final dimension.

3 If ’cold expansion’ transfer drill the fastener holes and open to the specific

starting hole diameter.

4 Cold expand the specified fastener holes on the reinforcement and structure

where no cracks were found.

Refer to SRM 51-30-47

Refer to FTI Tooling List No. FTI-A300-53-0389-1

Refer to Fig. A-GBPAA Sheet 03, Detail E, and Fig. A-GBPAA Sheet 05

5 Ream the specified fastener holes on the reinforcement and structure with the

correct gage finish reamer.

Refer to Fig. A-GBPAA Sheet 03, Detail E, and Fig. A-GBPAA Sheet 05

6 Remove the temporarily installed Item 40.

7 Clean the fastener holes with :

Solvent General

Purpose

11-026 As required

8 Install the reinforcement, Item 40, with :

27 Nut ASNA2528-3 Item 4

3 Nut ASNA2528-3A Item 5

11 Bolt EN6115K3-3 Item 6

16 Bolt EN6115K3X5 Item 10

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

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2 Bolt EN6115K3AX5 Item 12

1 Bolt EN6115K3AX3 Item 52

(b) If pins have been removed from the actuator beam at FR61, install new pins.

Refer to Fig. A-GBPAA Sheet 02, Detail B, Fig. A-GBPAA Sheet 05 and Fig. AGBPAA Sheet 06, Detail H

1 If nominal size pins have been removed from the actuator beam at FR61,

install new 1st oversize pins.

a Install :

7 Pin DAN5-6-6X Item 55

7 Collar DAN11-6X Item 16

2 If 1st oversize pins have been removed from the actuator beam at FR61,

install new 2nd oversize pins.

a Install :

7 Pin DAN5-6-6Y Item 56

7 Collar DAN11-6Y Item 57

(c) Install the reinforcement and brackets at the crossbeam at FR62.

Refer to Fig. A-GBPAA Sheet 02, Detail C, Fig. A-GBPAA Sheet 04, Detail G, and

Fig. A-GBPAA Sheet 05

1 At FR62 hold in position temporarily :

1 Bracket A5327415220600 Item 42

2 If a plastic cable support interferes with bracket, Item 42, replace the plastic

cable support with the following :

Refer to ESPM 20-33-11

1 Screw NAS1801-3-26 Item 70

2 Washer NAS1149D0332K Item 71

1 Spacer NSA5527-03-01D Item 72

1 Spacer NSA5527-03-08D Item 73

1 Nut MS21042-3 Item 74

1 Clamp MS21919WCH3 Item 75

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

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SERVICE BULLETIN

NOTE: The screw, Item 70, has to be installed from the AFT of the

FR62 and the clamp, Item 75, has to be orientated at 12

o’clock position (Up).

3 At FR62 install temporarily :

1 Reinforcement A5327429220600 Item 41

4 If no ’cold expansion’ drill the fastener holes and open to final dimension.

5 If ’cold expansion’ transfer drill the fastener holes and open to the specific

starting hole diameter.

6 Cold expand the specified fastener holes on the reinforcement and structure

where no cracks were found.

Refer to SRM 51-30-47

Refer to FTI Tooling List No. FTI-A300-53-0389-1

Refer to Fig. A-GBPAA Sheet 04, Detail G, and Fig. A-GBPAA Sheet 05

7 Ream the specified fastener holes on the reinforcement and structure with the

correct gage finish reamer.

Refer to Fig. A-GBPAA Sheet 04, Detail G, and Fig. A-GBPAA Sheet 05

8 Remove the temporarily installed Item 41.

9 Clean the fastener holes with :

Solvent General

Purpose

11-026 As required

10 Install the reinforcement, Item 41, with :

8 Nut ASNA2528-3 Item 4

12 Nut ASNA2528-3A Item 5

8 Bolt EN6115K3-3 Item 6

2 Bolt EN6115K3AX5 Item 12

10 Bolt EN6115K3A5 Item 51

11 At FR62 install :

1 Bracket A5327415220600 Item 42

with :

2 Rivet EN6081D6-09 Item 38

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

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SERVICE BULLETIN

12 At FR62 install :

1 Bracket A5327415220800 Item 43

with :

2 Rivet EN6081D4-07 Item 36

and :

1 Receptacle ABS0337-01A Item 45

with :

2 Rivet EN6069AD3-05 Item 50

13 Put in position at bracket, Item 43, and install :

NOTE: It is necessary to drill the hole to dia. 6.5mm (0.25in.) for

installation of the nut-plate, Item 44, during the installation of

the ceiling panel.

1 Nut-Plate MS21051L3 Item 44

with :

2 Rivet EN6069AD3-05 Item 50

14 Transfer drill the fastener holes and open to final dimension and close the two

holes with :

2 Rivet EN6081D6-09 Item 38

1 Rivet EN6069D4-05 Item 53

(d) Perform minor amendment of screws, spacers and split conduits (Refer to ESPM

20-33-11 and ESPM 20-33-33).

**CONF 002

(1) Subtask 530389-831-201-002 - Remove the existing fasteners from the crossbeam

at FR22 and FR23.

Work Zones and Access Panels

Zone Access/Work location

130

Manpower Resources

Manhours 4.00

Minimum number of person 2

Subtask elapsed time 2.00

Skills AIRFRAME

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

REVISION No.: 02 - Apr 27/11 Page: 42

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@A300

SERVICE BULLETIN

Material necessary to do the job

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Solvent General Purpose 11-026 As required

References

Consumable Material List (CML)

Fig. A-GBEAA

Removal of the Existing Fasteners from

the Crossbeam at FR22 and FR23

Sheet 01

Sheet 02

Sheet 03

Sheet 04

WARNING: BEFORE YOU REMOVE ANY RIVETS FROM THE CROSSBEAM FR22

OR FR23, ENSURE THAT THE FORWARD DOOR ACTUATOR IS

DISCONNECTED FROM THE ACTUATOR BEAM.

(a) Remove the fasteners from the crossbeam at FR22.

1 Remove the fasteners :

Refer to Fig. A-GBEAA Sheet 02, Detail B, and Fig. A-GBEAA Sheet 03,

Detail D

2 Clean the fasteners holes and the adjacent area with :

Solvent General

Purpose

11-026 As required

(b) If pins are installed in the actuator beam at FR22, remove them.

1 Remove the existing pins :

Refer to Fig. A-GBEAA Sheet 02, Detail B, and Fig. A-GBEAA Sheet 04,

Detail F

2 Clean the pin holes and the adjacent area with :

Solvent General

Purpose

11-026 As required

(c) Remove the fasteners from the crossbeam at FR23.

1 Remove the fasteners :

Refer to Fig. A-GBEAA Sheet 02, Detail C, and Fig. A-GBEAA Sheet 03,

Detail E

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

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@A300

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2 Clean the fastener holes and the adjacent area with :

Solvent General

Purpose

11-026 As required

(2) Subtask 530389-832-201-002 - Rotating Probe Inspection at the crossbeam at FR22

and FR23.

Work Zones and Access Panels

Zone Access/Work location

130

Manpower Resources

Manhours 4.00

Minimum number of person 1

Subtask elapsed time 4.00

Skills AIRFRAME

References

Non Destructive Test Manual (NTM) 51-30-10 PART 1

Fig. A-GBGAA

Installation of the Reinforcement at the

Crossbeam at FR22 and FR23

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

(a) Rotating Probe Inspection at the crossbeam at FR22.

1 Do a rotating probe inspection of the fastener holes at FR22 (Refer to NTM

51-30-10 PART 1).

Refer to Fig. A-GBGAA Sheet 03, Detail D

a If no crack(s) are found :

<1> - Refer to para. (3)(a).

b If crack(s) are found :

<1> Contact AIRBUS for further instructions.

(b) Rotating Probe Inspection at the crossbeam at FR23.

1 Do a rotating probe inspection of the fastener holes at FR23 (Refer to NTM

51-30-10 PART 1).

Refer to Fig. A-GBGAA Sheet 04, Detail F

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

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SERVICE BULLETIN

a If no crack(s) are found :

<1> - Refer to para. (3)(c).

b If crack(s) are found :

<1> Contact AIRBUS for further instructions.

(3) Subtask 530389-831-203-002 - Install the reinforcement at the crossbeam at FR22

and FR23.

Work Zones and Access Panels

Zone Access/Work location

130

Manpower Resources

Manhours 8.00

Minimum number of person 2

Subtask elapsed time 4.00

Skills AIRFRAME

Material necessary to do the job

Kit 530389D03R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

4 ASNA2528-3 32 NUT

5 ASNA2528-3A 14 NUT

6 EN6115K3-3 16 BOLT

9 EN6115K3X4 2 BOLT

10 EN6115K3X5 14 BOLT

12 EN6115K3AX5 2 BOLT

13 EN6115K3AX6 2 BOLT

14 EN6115K3A6 10 BOLT

16 DAN11-6X 7 COLLAR

20 A5378103420600 1 RNFRCMNT

21 A5378103422000 1 RNFRCMNT

55 DAN5-6-6X 7 PIN

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Solvent General Purpose 11-026 As required

References

Consumable Material List (CML)

Elec. Std. Practices Manual (ESPM) 20-33-11

20-33-33

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

REVISION No.: 02 - Apr 27/11 Page: 45

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@A300

SERVICE BULLETIN

References

Structural Repair Manual (SRM) 51-27-11

51-30-47

51-40-20

Fig. A-GBGAA

Installation of the Reinforcement at the

Crossbeam at FR22 and FR23

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

(a) Install the reinforcement at the crossbeam at FR22.

Refer to Fig. A-GBGAA Sheet 02, Detail B, Fig. A-GBGAA Sheet 03, Detail E, Fig.

A-GBGAA Sheet 05, Fig. A-GBGAA Sheet 07, Detail J and K and Fig. A-GBGAA

Sheet 08, Detail L and M

1 If the reinforcement, Item 20, has been delivered with the old contour, rework

the reinforcement to the new contour to avoid any interference with a plastic

cable support.

Refer to SRM 51-27-11

Refer to Fig. A-GBGAA Sheet 07, Details J and K

2 If the reinforcement, Item 20, has been delivered with the old contour and if it

has any interference with a plastic cable support on the inboard side, rework

the reinforcement to the new contour.

Refer to SRM 51-27-11

Refer to Fig. A-GBGAA Sheet 08, Details L and M

3 At FR22 install temporarily :

1 Reinforcement A5378103420600 Item 20

4 If no ’cold expansion’ drill the fastener holes and open to final dimension.

5 If ’cold expansion’ transfer drill the fastener holes and open to the specific

starting hole diameter.

6 Cold expand the specified fastener holes on the reinforcement and structure

where no cracks were found.

Refer to SRM 51-30-47

Refer to FTI Tooling List No. FTI-A300-53-0389-1

Refer to Fig. A-GBGAA Sheet 03, Detail E, and Fig. A-GBGAA Sheet 05

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

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7 Ream the specified fastener holes on the reinforcement and structure with the

correct gage finish reamer.

Refer to Fig. A-GBGAA Sheet 03, Detail E, and Fig. A-GBGAA Sheet 05

8 Remove the temporarily installed Item 20.

9 Clean the fastener holes with :

Solvent General

Purpose

11-026 As required

10 Install the reinforcement, Item 20, with :

22 Nut ASNA2528-3 Item 4

2 Nut ASNA2528-3A Item 5

6 Bolt EN6115K3-3 Item 6

2 Bolt EN6115K3X4 Item 9

14 Bolt EN6115K3X5 Item 10

2 Bolt EN6115K3AX5 Item 12

(b) If nominal size pins have been removed from the actuator beam at FR22, install

new 1st oversize pins.

Refer to Fig. A-GBGAA Sheet 02, Detail B, Fig. A-GBGAA Sheet 05 and Fig. AGBGAA Sheet 06, Detail H

1 Install :

7 Pin DAN5-6-6X Item 55

7 Collar DAN11-6X Item 16

(c) Install the reinforcement at the crossbeam at FR23.

Refer to Fig. A-GBGAA Sheet 02, Detail C, Fig. A-GBGAA Sheet 04, Detail G, and

Fig. A-GBGAA Sheet 05

1 At FR22 install temporarily :

1 Reinforcement A5378103422000 Item 21

2 If no ’cold expansion’ drill the fastener holes and open to final dimension.

3 If ’cold expansion’ transfer drill the fastener holes and open to the specific

starting hole diameter.

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

REVISION No.: 02 - Apr 27/11 Page: 47

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@A300

SERVICE BULLETIN

4 Cold expand the specified fastener holes where no cracks were found.

Refer to SRM 51-30-47

Refer to FTI Tooling List No. FTI-A300-53-0389-1

Refer to Fig. A-GBGAA Sheet 04, Detail G, and Fig. A-GBGAA Sheet 05

5 Ream the specified fastener holes on the structure and reinforcement with the

correct gage finish reamer.

Refer toFig. A-GBGAA Sheet 04, Detail G, and Fig. A-GBGAA Sheet 05

6 Remove the temporarily installed Item 21.

7 Clean the fastener holes with :

Solvent General

Purpose

11-026 As required

8 Install the reinforcement, Item 21, with :

10 Nut ASNA2528-3 Item 4

12 Nut ASNA2528-3A Item 5

10 Bolt EN6115K3-3 Item 6

2 Bolt EN6115K3AX6 Item 13

10 Bolt EN6115K3A6 Item 14

(d) Perform minor amendment of screws, spacers and split conduits (Refer to ESPM

20-33-11 and ESPM 20-33-33).

(4) Subtask 530389-831-205-001 - Remove the existing fasteners from the crossbeam

FR61 and FR62.

Work Zones and Access Panels

Zone Access/Work location

150

Manpower Resources

Manhours 3.00

Minimum number of person 2

Subtask elapsed time 1.50

Skills AIRFRAME

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

REVISION No.: 02 - Apr 27/11 Page: 48

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@A300

SERVICE BULLETIN

Material necessary to do the job

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Solvent General Purpose 11-026 As required

References

Consumable Material List (CML)

Fig. A-GBNAA

Removal of the Existing Rivets from the

Crossbeam at FR61 and FR62

Sheet 01

Sheet 02

Sheet 03

Sheet 04

WARNING: BEFORE YOU REMOVE ANY RIVETS FROM THE CROSSBEAM

FR61 OR FR62, ENSURE THAT THE AFTER DOOR ACTUATOR IS

DISCONNECTED FROM THE ACTUATOR BEAM.

(a) Remove the existing fasteners from the crossbeam FR61.

1 Remove the existing fasteners :

Refer to Fig. A-GBNAA Sheet 02, Detail B, and Fig. A-GBNAA Sheet 03,

Detail D

2 Clean the fasteners holes and the adjacent area with :

Solvent General

Purpose

11-026 As required

(b) If pins are installed in the actuator beam at FR61, remove them.

1 Remove the existing pins :

Refer to Fig. A-GBNAA Sheet 02, Detail B, and Fig. A-GBNAA Sheet 04,

Detail F

2 Clean the pin holes and the adjacent area with :

Solvent General

Purpose

11-026 As required

(c) Remove the existing fasteners from the crossbeam FR62.

1 Remove the bracket, the receptacle and the fasteners :

Refer to Fig. A-GBNAA Sheet 02, Detail C, and Fig. A-GBNAA Sheet 03,

Detail E

1 Bracket A2557309120600 Item (43) Discard

1 Nut NAS1068C3 Item (44) Discard

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

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1 Receptacle DAN367-01 Item (45) Discard

2 Clean the fastener holes and the adjacent area with :

Solvent General

Purpose

11-026 As required

(5) Subtask 530389-831-206-001 - Rotating Probe Inspection at the crossbeam FR61

and FR62.

Work Zones and Access Panels

Zone Access/Work location

150

Manpower Resources

Manhours 4.00

Minimum number of person 1

Subtask elapsed time 4.00

Skills AIRFRAME

References

Consumable Material List (CML)

Non Destructive Test Manual (NTM) 51-30-10 PART 1

Fig. A-GBPAA

Installation of the Reinforcement at the

Crossbeam at FR61 and FR62

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

(a) Rotating Probe Inspection at the crossbeam at FR61.

1 Do a rotating probe inspection of the fastener holes at FR61 (Refer to NTM

51-30-10 PART 1).

Refer to Fig. A-GBPAA Sheet 03, Detail D

a If no crack(s) are found :

<1> - Refer to para. (6)(a).

b If crack(s) are found :

<1> Contact AIRBUS for further instructions.

(b) Rotating Probe Inspection at the crossbeam at FR62.

1 Do a rotating probe inspection of the fastener holes at FR62 (Refer to NTM

51-30-10 PART 1).

Refer to Fig. A-GBPAA Sheet 04, Detail F

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

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a If no crack(s) are found :

<1> - Refer to para. (6)(c).

b If crack(s) are found :

<1> Contact AIRBUS for further instructions.

(6) Subtask 530389-831-207-001 - Install the reinforcement and brackets at the

crossbeam at FR61 and FR62.

Work Zones and Access Panels

Zone Access/Work location

150

Manpower Resources

Manhours 6.00

Minimum number of person 2

Subtask elapsed time 3.00

Skills AIRFRAME

Material necessary to do the job

Kit 530389D01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

4 ASNA2528-3 35 NUT

5 ASNA2528-3A 15 NUT

6 EN6115K3-3 19 BOLT

10 EN6115K3X5 16 BOLT

12 EN6115K3AX5 4 BOLT

16 DAN11-6X 7 COLLAR

36 EN6081D4-07 2 RIVET

38 EN6081D6-09 4 RIVET

40 A5327429220000 1 PLATE

41 A5327429220600 1 PLATE

42 A5327415220600 1 ANGLE

43 A5327415220800 1 ANGLE

44 MS21051L3 1 NUT

45 ABS0337-01A 1 RECEPTCL

50 EN6069AD3-05 4 RIVET

51 EN6115K3A5 10 BOLT

52 EN6115K3AX3 1 BOLT

53 EN6069D4-05 1 RIVET

55 DAN5-6-6X 7 PIN

56 DAN5-6-6Y 7 PIN

57 DAN11-6Y 7 COLLAR

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

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Component COMPD01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

70 NAS1801-3-26 1 SCREW

71 NAS1149D0332K 2 WASHER

72 NSA5527-03-01D 1 SPACER

73 NSA5527-03-08D 1 SPACER

74 MS21042-3 1 NUT

75 MS21919WCH3 1 CLAMP

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Solvent General Purpose 11-026 As required

References

Consumable Material List (CML)

Elec. Std. Practices Manual (ESPM) 20-33-11

20-33-33

Structural Repair Manual (SRM) 51-30-47

Fig. A-GBPAA

Installation of the Reinforcement at the

Crossbeam at FR61 and FR62

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

(a) Install the reinforcement at the crossbeam at FR61.

Refer to Fig. A-GBPAA Sheet 02, Detail B, Fig. A-GBPAA Sheet 03, Detail E, and

Fig. A-GBPAA Sheet 05

1 At FR61 install temporarily :

1 Reinforcement A5327429220000 Item 40

2 If no ’cold expansion’ drill the fastener holes and open to final dimension.

3 If ’cold expansion’ transfer drill the fastener holes and open to the specific

starting hole diameter.

4 Cold expand the specified fastener holes on the reinforcement and structure

where no cracks were found.

Refer to SRM 51-30-47

Refer to FTI Tooling List No. FTI-A300-53-0389-1

Refer to Fig. A-GBPAA Sheet 03, Detail E, and Fig. A-GBPAA Sheet 05

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

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5 Ream the specified fastener holes on the reinforcement and structure with the

correct gage finish reamer.

Refer to Fig. A-GBPAA Sheet 03, Detail E, and Fig. A-GBPAA Sheet 05

6 Remove the temporarily installed Item 40.

7 Clean the fastener holes with :

Solvent General

Purpose

11-026 As required

8 Install the reinforcement, Item 40, with :

27 Nut ASNA2528-3 Item 4

3 Nut ASNA2528-3A Item 5

11 Bolt EN6115K3-3 Item 6

16 Bolt EN6115K3X5 Item 10

2 Bolt EN6115K3AX5 Item 12

1 Bolt EN6115K3AX3 Item 52

(b) If pins have been removed from the actuator beam at FR61, install new pins.

Refer to Fig. A-GBPAA Sheet 02, Detail B, Fig. A-GBPAA Sheet 05 and Fig. AGBPAA Sheet 06, Detail H

1 If nominal size pins have been removed from the actuator beam at FR61,

install new 1st oversize pins.

a Install :

7 Pin DAN5-6-6X Item 55

7 Collar DAN11-6X Item 16

2 If 1st oversize pins have been removed from the actuator beam at FR61,

install new 2nd oversize pins.

a Install :

7 Pin DAN5-6-6Y Item 56

7 Collar DAN11-6Y Item 57

(c) Install the reinforcement and brackets at the crossbeam at FR62.

Refer to Fig. A-GBPAA Sheet 02, Detail C, Fig. A-GBPAA Sheet 04, Detail G, and

Fig. A-GBPAA Sheet 05

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

REVISION No.: 02 - Apr 27/11 Page: 53

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@A300

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1 At FR62 hold in position temporarily :

1 Bracket A5327415220600 Item 42

2 If a plastic cable support interferes with bracket, Item 42, replace the plastic

cable support with the following :

Refer to ESPM 20-33-11

1 Screw NAS1801-3-26 Item 70

2 Washer NAS1149D0332K Item 71

1 Spacer NSA5527-03-01D Item 72

1 Spacer NSA5527-03-08D Item 73

1 Nut MS21042-3 Item 74

1 Clamp MS21919WCH3 Item 75

NOTE: The screw, Item 70, has to be installed from the AFT of the

FR62 and the clamp, Item 75, has to be orientated at 12

o’clock position (Up).

3 At FR62 install temporarily :

1 Reinforcement A5327429220600 Item 41

4 If no ’cold expansion’ drill the fastener holes and open to final dimension.

5 If ’cold expansion’ transfer drill the fastener holes and open to the specific

starting hole diameter.

6 Cold expand the specified fastener holes on the reinforcement and structure

where no cracks were found.

Refer to SRM 51-30-47

Refer to FTI Tooling List No. FTI-A300-53-0389-1

Refer to Fig. A-GBPAA Sheet 04, Detail G, and Fig. A-GBPAA Sheet 05

7 Ream the specified fastener holes on the reinforcement and structure with the

correct gage finish reamer.

Refer to Fig. A-GBPAA Sheet 04, Detail G, and Fig. A-GBPAA Sheet 05

8 Remove the temporarily installed Item 41.

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

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9 Clean the fastener holes with :

Solvent General

Purpose

11-026 As required

10 Install the reinforcement, Item 41, with :

8 Nut ASNA2528-3 Item 4

12 Nut ASNA2528-3A Item 5

8 Bolt EN6115K3-3 Item 6

2 Bolt EN6115K3AX5 Item 12

10 Bolt EN6115K3A5 Item 51

11 At FR62 install :

1 Bracket A5327415220600 Item 42

with :

2 Rivet EN6081D6-09 Item 38

12 At FR62 install :

1 Bracket A5327415220800 Item 43

with :

2 Rivet EN6081D4-07 Item 36

and :

1 Receptacle ABS0337-01A Item 45

with :

2 Rivet EN6069AD3-05 Item 50

13 Put in position at bracket, Item 43, and install :

NOTE: It is necessary to drill the hole to dia. 6.5mm (0.25in.) for

installation of the nut-plate, Item 44, during the installation of

the ceiling panel.

1 Nut-Plate MS21051L3 Item 44

with :

2 Rivet EN6069AD3-05 Item 50

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SERVICE BULLETIN

14 Transfer drill the fastener holes and open to final dimension and close the two

holes with :

2 Rivet EN6081D6-09 Item 38

1 Rivet EN6069D4-05 Item 53

(d) Perform minor amendment of screws, spacers and split conduits (Refer to ESPM

20-33-11 and ESPM 20-33-33).

**CONF 003

(1) Subtask 530389-831-201-003 - Remove the existing fasteners and the brackets

from the crossbeam at FR22 and FR23.

Work Zones and Access Panels

Zone Access/Work location

130

Manpower Resources

Manhours 4.00

Minimum number of person 2

Subtask elapsed time 2.00

Skills AIRFRAME

Material necessary to do the job

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Solvent General Purpose 11-026 As required

References

Consumable Material List (CML)

Structural Repair Manual (SRM) 53-13-00

Fig. A-GBJAA

Removal of the Existing Fasteners from

the Crossbeam at FR22 and FR23

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

WARNING: BEFORE YOU REMOVE ANY RIVETS FROM THE CROSSBEAM FR22

OR FR23, ENSURE THAT THE FORWARD DOOR ACTUATOR IS

DISCONNECTED FROM THE ACTUATOR BEAM.

(a) Remove the existing fasteners and the brackets from the crossbeam at FR22.

1 Remove the existing fasteners and the brackets :

Refer to Fig. A-GBJAA Sheet 02, Detail B, and Fig. A-GBJAA Sheet 04, Detail

D

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1 Bracket A5377469720000 Item (25) Retain

1 Console A2557105700000 Item (26) Retain

1 Bracket A9249602920000 Item (27) Retain

1 Bracket A5377466620000 Item (28) Retain

2 Rework the affected area as shown in Fig. A-GBJAA Sheet 02, Detail B, Fig.

A-GBJAA Sheet 03, Detail C, and Section A-A

Refer to SRM 53-13-00

3 Clean the fastener holes and the adjacent area with :

Solvent General

Purpose

11-026 As required

(b) If pins are installed in the actuator beam at FR22, remove them.

1 Remove the existing pins :

Refer to Fig. A-GBJAA Sheet 02, Detail B, and Fig. A-GBJAA Sheet 05, Detail

G

2 Clean the pin holes and the adjacent area with :

Solvent General

Purpose

11-026 As required

(c) Remove the existing fasteners from the crossbeam at FR23.

1 Remove the existing fasteners :

Refer to Fig. A-GBJAA Sheet 04, Details E and F

2 Clean the fastener holes and the adjacent area with :

Solvent General

Purpose

11-026 As required

(2) Subtask 530389-832-201-003 - Rotating Probe Inspection at the crossbeam at FR22

and FR23.

Work Zones and Access Panels

Zone Access/Work location

130

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

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SERVICE BULLETIN

Manpower Resources

Manhours 4.00

Minimum number of person 1

Subtask elapsed time 4.00

Skills AIRFRAME

References

Non Destructive Test Manual (NTM) 51-30-10 PART 1

Fig. A-GBLAA

Installation of the Reinforcement at the

Crossbeam at FR22 and FR23

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

(a) Rotating Probe Inspection at the crossbeam at FR22.

1 Do a rotating probe inspection of the fastener holes at FR22 (Refer to NTM

51-30-10 PART 1).

Refer to Fig. A-GBLAA Sheet 03, Detail C

a If no crack(s) are found :

<1> - Refer to para. (3)(a).

b If crack(s) are found :

<1> Contact AIRBUS for further instructions.

(b) Rotating Probe Inspection at the crossbeam at FR23.

1 Do a rotating probe inspection of the fastener holes at FR23 (Refer to NTM

51-30-10 PART 1).

Refer to Fig. A-GBLAA Sheet 04, Detail F

a If no crack(s) are found :

<1> - Refer to para. (3)(c).

b If crack(s) are found :

<1> Contact AIRBUS for further instructions.

(3) Subtask 530389-831-203-003 - Install the reinforcement and the brackets at the

crossbeam at FR22 and FR23.

Work Zones and Access Panels

Zone Access/Work location

130

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

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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

Kit 530389D04R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

4 ASNA2528-3 28 NUT

5 ASNA2528-3A 8 NUT

8 EN6115K3-5 2 BOLT

10 EN6115K3X5 6 BOLT

13 EN6115K3AX6 2 BOLT

16 DAN11-6X 7 COLLAR

22 A5378103423400 1 RNFRCMNT

23 MS21076L4N 2 NUT

25 A5377469720000 1 ANGLE

30 EN6115K3X6 10 BOLT

31 EN6115K3X7 10 BOLT

32 EN6115K3AX7 6 BOLT

35 EN6081D3-06 4 RIVET

36 EN6081D4-07 4 RIVET

37 EN6081D5-07 4 RIVET

38 EN6081D6-07 18 RIVET

55 DAN5-6-6X 7 PIN

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Solvent General Purpose 11-026 As required

References

Consumable Material List (CML)

Elec. Std. Practices Manual (ESPM) 20-33-11

20-33-33

Structural Repair Manual (SRM) 51-30-47

Fig. A-GBLAA

Installation of the Reinforcement at the

Crossbeam at FR22 and FR23

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

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(a) Install the reinforcement and the brackets at the crossbeam at FR22.

Refer to Fig. A-GBLAA Sheet 02, Detail B, Fig. A-GBLAA Sheet 03, Detail D, and

Fig. A-GBLAA Sheet 05

1 At FR22 install temporarily :

1 Reinforcement A5378103423400 Item 22

1 Bracket A5377469720000 Item 25

1 Bracket A5377466620000 Item (28) Retained at

removal

2 If no ’cold expansion’ drill the fastener holes and open to final dimension.

3 If ’cold expansion’ transfer drill the fastener holes and open to the specific

starting hole diameter.

4 Cold expand the specified fastener holes where no cracks were found.

Refer to SRM 51-30-47

Refer to FTI Tooling List No. FTI-A300-53-0389-1

Refer to Fig. A-GBLAA Sheet 03, Detail D, and Fig. A-GBLAA Sheet 05

5 Ream the specified fastener holes on the structure and reinforcement with the

correct gage finish reamer.

Refer to Fig. A-GBLAA Sheet 03, Detail D, and Fig. A-GBLAA Sheet 05

6 Remove the temporarily installed Items 22, 25 and 28.

7 Clean the fastener holes with :

Solvent General

Purpose

11-026 As required

8 Install the reinforcement, Item 22, the bracket, Item 25, and the bracket, Item

28, with :

16 Nut ASNA2528-3 Item 4

6 Nut ASNA2528-3A Item 5

6 Bolt EN6115K3X5 Item 10

2 Bolt EN6115K3AX6 Item 13

10 Bolt EN6115K3X6 Item 30

4 Bolt EN6115K3AX7 Item 32

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18 Rivet EN6081D6-07 Item 38

9 At FR22 install temporarily :

2 Console A2557105700000 Item (26) Retained at

removal

10 Transfer drill the fastener holes and open to final dimension.

11 Install the temporarily installed Item (26) with :

4 Rivet EN6081D5-07 Item 37

12 At FR22, at Item (26), install :

2 Nut MS21076L4N Item 23

4 Rivet EN6081D3-06 Item 35

13 At FR22 install temporarily :

1 Bracket A9249602920000 Item (27)

14 Transfer drill the fastener holes and open to final dimension.

15 Install the temporarily installed item (27) with :

4 Rivet EN6081D4-07 Item 36

(b) If nominal size pins have been removed from the actuator beam at FR22, install

new 1st oversize pins.

Refer to Fig. A-GBLAA Sheet 02, Detail B, Fig. A-GBLAA Sheet 05 and Fig. AGBLAA Sheet 06, Detail H

1 Install :

7 Pin DAN5-6-6X Item 55

7 Collar DAN11-6X Item 16

(c) Install the fasteners at the crossbeam at FR23.

Refer to Fig. A-GBLAA Sheet 02, Detail C, Fig. A-GBLAA Sheet 04, Details E and

G, and Fig. A-GBLAA Sheet 05

1 At FR23, if no ’cold expansion’ drill the fastener holes and open to final

dimension.

2 At FR23, if ’cold expansion’ transfer drill the fastener holes and open to the

specific starting hole diameter.

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

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3 Cold expand the specified fastener holes where no cracks were found.

Refer to SRM 51-30-47

Refer to FTI Tooling List No. FTI-A300-53-0389-1

Refer to Fig. A-GBLAA Sheet 04, Details E and G, and Fig. A-GBLAA Sheet

05

4 Ream the specified fastener holes on the structure and reinforcement with the

correct gage finish reamer.

5 Clean the fastener holes with :

Refer to Fig. A-GBLAA Sheet 04, Details E and G, and Fig. A-GBLAA Sheet

05

Solvent General

Purpose

11-026 As required

6 Install items :

12 Nut ASNA2528-3 Item 4

2 Nut ASNA2528-3A Item 5

2 Bolt EN6115K3-5 Item 8

10 Bolt EN6115K3X7 Item 31

2 Bolt EN6115K3AX7 Item 32

(d) Perform minor amendment of screws, spacers and split conduits (Refer to ESPM

20-33-11 and ESPM 20-33-33).

(4) Subtask 530389-831-205-001 - Remove the existing fasteners from the crossbeam

FR61 and FR62.

Work Zones and Access Panels

Zone Access/Work location

150

Manpower Resources

Manhours 3.00

Minimum number of person 2

Subtask elapsed time 1.50

Skills AIRFRAME

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

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Material necessary to do the job

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Solvent General Purpose 11-026 As required

References

Consumable Material List (CML)

Fig. A-GBNAA

Removal of the Existing Rivets from the

Crossbeam at FR61 and FR62

Sheet 01

Sheet 02

Sheet 03

Sheet 04

WARNING: BEFORE YOU REMOVE ANY RIVETS FROM THE CROSSBEAM

FR61 OR FR62, ENSURE THAT THE AFTER DOOR ACTUATOR IS

DISCONNECTED FROM THE ACTUATOR BEAM.

(a) Remove the existing fasteners from the crossbeam FR61.

1 Remove the existing fasteners :

Refer to Fig. A-GBNAA Sheet 02, Detail B, and Fig. A-GBNAA Sheet 03,

Detail D

2 Clean the fasteners holes and the adjacent area with :

Solvent General

Purpose

11-026 As required

(b) If pins are installed in the actuator beam at FR61, remove them.

1 Remove the existing pins :

Refer to Fig. A-GBNAA Sheet 02, Detail B, and Fig. A-GBNAA Sheet 04,

Detail F

2 Clean the pin holes and the adjacent area with :

Solvent General

Purpose

11-026 As required

(c) Remove the existing fasteners from the crossbeam FR62.

1 Remove the bracket, the receptacle and the fasteners :

Refer to Fig. A-GBNAA Sheet 02, Detail C, and Fig. A-GBNAA Sheet 03,

Detail E

1 Bracket A2557309120600 Item (43) Discard

1 Nut NAS1068C3 Item (44) Discard

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

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SERVICE BULLETIN

1 Receptacle DAN367-01 Item (45) Discard

2 Clean the fastener holes and the adjacent area with :

Solvent General

Purpose

11-026 As required

(5) Subtask 530389-831-206-001 - Rotating Probe Inspection at the crossbeam FR61

and FR62.

Work Zones and Access Panels

Zone Access/Work location

150

Manpower Resources

Manhours 4.00

Minimum number of person 1

Subtask elapsed time 4.00

Skills AIRFRAME

References

Consumable Material List (CML)

Non Destructive Test Manual (NTM) 51-30-10 PART 1

Fig. A-GBPAA

Installation of the Reinforcement at the

Crossbeam at FR61 and FR62

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

(a) Rotating Probe Inspection at the crossbeam at FR61.

1 Do a rotating probe inspection of the fastener holes at FR61 (Refer to NTM

51-30-10 PART 1).

Refer to Fig. A-GBPAA Sheet 03, Detail D

a If no crack(s) are found :

<1> - Refer to para. (6)(a).

b If crack(s) are found :

<1> Contact AIRBUS for further instructions.

(b) Rotating Probe Inspection at the crossbeam at FR62.

1 Do a rotating probe inspection of the fastener holes at FR62 (Refer to NTM

51-30-10 PART 1).

Refer to Fig. A-GBPAA Sheet 04, Detail F

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a If no crack(s) are found :

<1> - Refer to para. (6)(c).

b If crack(s) are found :

<1> Contact AIRBUS for further instructions.

(6) Subtask 530389-831-207-001 - Install the reinforcement and brackets at the

crossbeam at FR61 and FR62.

Work Zones and Access Panels

Zone Access/Work location

150

Manpower Resources

Manhours 6.00

Minimum number of person 2

Subtask elapsed time 3.00

Skills AIRFRAME

Material necessary to do the job

Kit 530389D01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

4 ASNA2528-3 35 NUT

5 ASNA2528-3A 15 NUT

6 EN6115K3-3 19 BOLT

10 EN6115K3X5 16 BOLT

12 EN6115K3AX5 4 BOLT

16 DAN11-6X 7 COLLAR

36 EN6081D4-07 2 RIVET

38 EN6081D6-09 4 RIVET

40 A5327429220000 1 PLATE

41 A5327429220600 1 PLATE

42 A5327415220600 1 ANGLE

43 A5327415220800 1 ANGLE

44 MS21051L3 1 NUT

45 ABS0337-01A 1 RECEPTCL

50 EN6069AD3-05 4 RIVET

51 EN6115K3A5 10 BOLT

52 EN6115K3AX3 1 BOLT

53 EN6069D4-05 1 RIVET

55 DAN5-6-6X 7 PIN

56 DAN5-6-6Y 7 PIN

57 DAN11-6Y 7 COLLAR

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SERVICE BULLETIN

Component COMPD01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

70 NAS1801-3-26 1 SCREW

71 NAS1149D0332K 2 WASHER

72 NSA5527-03-01D 1 SPACER

73 NSA5527-03-08D 1 SPACER

74 MS21042-3 1 NUT

75 MS21919WCH3 1 CLAMP

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Solvent General Purpose 11-026 As required

References

Consumable Material List (CML)

Elec. Std. Practices Manual (ESPM) 20-33-11

20-33-33

Structural Repair Manual (SRM) 51-30-47

Fig. A-GBPAA

Installation of the Reinforcement at the

Crossbeam at FR61 and FR62

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

(a) Install the reinforcement at the crossbeam at FR61.

Refer to Fig. A-GBPAA Sheet 02, Detail B, Fig. A-GBPAA Sheet 03, Detail E, and

Fig. A-GBPAA Sheet 05

1 At FR61 install temporarily :

1 Reinforcement A5327429220000 Item 40

2 If no ’cold expansion’ drill the fastener holes and open to final dimension.

3 If ’cold expansion’ transfer drill the fastener holes and open to the specific

starting hole diameter.

4 Cold expand the specified fastener holes on the reinforcement and structure

where no cracks were found.

Refer to SRM 51-30-47

Refer to FTI Tooling List No. FTI-A300-53-0389-1

Refer to Fig. A-GBPAA Sheet 03, Detail E, and Fig. A-GBPAA Sheet 05

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5 Ream the specified fastener holes on the reinforcement and structure with the

correct gage finish reamer.

Refer to Fig. A-GBPAA Sheet 03, Detail E, and Fig. A-GBPAA Sheet 05

6 Remove the temporarily installed Item 40.

7 Clean the fastener holes with :

Solvent General

Purpose

11-026 As required

8 Install the reinforcement, Item 40, with :

27 Nut ASNA2528-3 Item 4

3 Nut ASNA2528-3A Item 5

11 Bolt EN6115K3-3 Item 6

16 Bolt EN6115K3X5 Item 10

2 Bolt EN6115K3AX5 Item 12

1 Bolt EN6115K3AX3 Item 52

(b) If pins have been removed from the actuator beam at FR61, install new pins.

Refer to Fig. A-GBPAA Sheet 02, Detail B, Fig. A-GBPAA Sheet 05 and Fig. AGBPAA Sheet 06, Detail H

1 If nominal size pins have been removed from the actuator beam at FR61,

install new 1st oversize pins.

a Install :

7 Pin DAN5-6-6X Item 55

7 Collar DAN11-6X Item 16

2 If 1st oversize pins have been removed from the actuator beam at FR61,

install new 2nd oversize pins.

a Install :

7 Pin DAN5-6-6Y Item 56

7 Collar DAN11-6Y Item 57

(c) Install the reinforcement and brackets at the crossbeam at FR62.

Refer to Fig. A-GBPAA Sheet 02, Detail C, Fig. A-GBPAA Sheet 04, Detail G, and

Fig. A-GBPAA Sheet 05

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@A300

SERVICE BULLETIN

1 At FR62 hold in position temporarily :

1 Bracket A5327415220600 Item 42

2 If a plastic cable support interferes with bracket, Item 42, replace the plastic

cable support with the following :

Refer to ESPM 20-33-11

1 Screw NAS1801-3-26 Item 70

2 Washer NAS1149D0332K Item 71

1 Spacer NSA5527-03-01D Item 72

1 Spacer NSA5527-03-08D Item 73

1 Nut MS21042-3 Item 74

1 Clamp MS21919WCH3 Item 75

NOTE: The screw, Item 70, has to be installed from the AFT of the

FR62 and the clamp, Item 75, has to be orientated at 12

o’clock position (Up).

3 At FR62 install temporarily :

1 Reinforcement A5327429220600 Item 41

4 If no ’cold expansion’ drill the fastener holes and open to final dimension.

5 If ’cold expansion’ transfer drill the fastener holes and open to the specific

starting hole diameter.

6 Cold expand the specified fastener holes on the reinforcement and structure

where no cracks were found.

Refer to SRM 51-30-47

Refer to FTI Tooling List No. FTI-A300-53-0389-1

Refer to Fig. A-GBPAA Sheet 04, Detail G, and Fig. A-GBPAA Sheet 05

7 Ream the specified fastener holes on the reinforcement and structure with the

correct gage finish reamer.

Refer to Fig. A-GBPAA Sheet 04, Detail G, and Fig. A-GBPAA Sheet 05

8 Remove the temporarily installed Item 41.

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9 Clean the fastener holes with :

Solvent General

Purpose

11-026 As required

10 Install the reinforcement, Item 41, with :

8 Nut ASNA2528-3 Item 4

12 Nut ASNA2528-3A Item 5

8 Bolt EN6115K3-3 Item 6

2 Bolt EN6115K3AX5 Item 12

10 Bolt EN6115K3A5 Item 51

11 At FR62 install :

1 Bracket A5327415220600 Item 42

with :

2 Rivet EN6081D6-09 Item 38

12 At FR62 install :

1 Bracket A5327415220800 Item 43

with :

2 Rivet EN6081D4-07 Item 36

and :

1 Receptacle ABS0337-01A Item 45

with :

2 Rivet EN6069AD3-05 Item 50

13 Put in position at bracket, Item 43, and install :

NOTE: It is necessary to drill the hole to dia. 6.5mm (0.25in.) for

installation of the nut-plate, Item 44, during the installation of

the ceiling panel.

1 Nut-Plate MS21051L3 Item 44

with :

2 Rivet EN6069AD3-05 Item 50

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

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@A300

SERVICE BULLETIN

14 Transfer drill the fastener holes and open to final dimension and close the two

holes with :

2 Rivet EN6081D6-09 Item 38

1 Rivet EN6069D4-05 Item 53

(d) Perform minor amendment of screws, spacers and split conduits (Refer to ESPM

20-33-11 and ESPM 20-33-33).

**CONF ALL

D. TEST

**CONF 001

(1) Subtask 530389-700-201-001 - Test

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 52-30-00, Page Block 301

52-31-11, Page Block 501

52-33-11, Page Block 501

52-33-18, Page Block 401

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) Install the FWD cargo-compartment door actuator on the support beam (Refer to

AMM 52-33-18, Page Block 401).

(c) Install the AFT cargo-compartment door actuator on the support beam (Refer to

AMM 52-33-18, Page Block 401).

(d) Make sure that the applicable cargo-door safety-equipment is removed from the

FWD and AFT cargo-compartment doors (Refer to AMM 52-30-00, Page Block

301).

(e) Remove the safety clip(s) and tag(s) and close this (these) circuit breaker(s) :

PANEL DESIGNATION FIN LOCATION SEE

NOTES

128VU HYDRAULIC/ACCU PRESS

CTL AND CARGO PUMP

7GX 803/C11

101VU ELEC HYD PUMP 23GX ALT2

NOTE: The location of the circuit breaker(s) can be different from the

location given in the table.

(f) Adjust the FWD and AFT door actuator and do a functional test (Refer to AMM

52-33-18, Page Block 401).

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

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@A300

SERVICE BULLETIN

**CONF 002

(1) Subtask 530389-700-201-001 - Test

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 52-30-00, Page Block 301

52-31-11, Page Block 501

52-33-11, Page Block 501

52-33-18, Page Block 401

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) Install the FWD cargo-compartment door actuator on the support beam (Refer to

AMM 52-33-18, Page Block 401).

(c) Install the AFT cargo-compartment door actuator on the support beam (Refer to

AMM 52-33-18, Page Block 401).

(d) Make sure that the applicable cargo-door safety-equipment is removed from the

FWD and AFT cargo-compartment doors (Refer to AMM 52-30-00, Page Block

301).

(e) Remove the safety clip(s) and tag(s) and close this (these) circuit breaker(s) :

PANEL DESIGNATION FIN LOCATION SEE

NOTES

128VU HYDRAULIC/ACCU PRESS

CTL AND CARGO PUMP

7GX 803/C11

101VU ELEC HYD PUMP 23GX ALT2

NOTE: The location of the circuit breaker(s) can be different from the

location given in the table.

(f) Adjust the FWD and AFT door actuator and do a functional test (Refer to AMM

52-33-18, Page Block 401).

**CONF 003

(1) Subtask 530389-700-201-001 - Test

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 52-30-00, Page Block 301

52-31-11, Page Block 501

52-33-11, Page Block 501

52-33-18, Page Block 401

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

REVISION No.: 02 - Apr 27/11 Page: 71

6

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@A300

SERVICE BULLETIN

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) Install the FWD cargo-compartment door actuator on the support beam (Refer to

AMM 52-33-18, Page Block 401).

(c) Install the AFT cargo-compartment door actuator on the support beam (Refer to

AMM 52-33-18, Page Block 401).

(d) Make sure that the applicable cargo-door safety-equipment is removed from the

FWD and AFT cargo-compartment doors (Refer to AMM 52-30-00, Page Block

301).

(e) Remove the safety clip(s) and tag(s) and close this (these) circuit breaker(s) :

PANEL DESIGNATION FIN LOCATION SEE

NOTES

128VU HYDRAULIC/ACCU PRESS

CTL AND CARGO PUMP

7GX 803/C11

101VU ELEC HYD PUMP 23GX ALT2

NOTE: The location of the circuit breaker(s) can be different from the

location given in the table.

(f) Adjust the FWD and AFT door actuator and do a functional test (Refer to AMM

52-33-18, Page Block 401).

**CONF ALL

E. CLOSE-UP

**CONF 001

(1) Subtask 530389-942-201-001 - Close-up

Manpower Resources

Skills AIRFRAME

References

Aircraft Maintenance Manual (AMM) 06-21-53, Page Block 001

25-51-11, Page Block 401

25-52-11, Page Block 401

52-30-00, Page Block 301

(a) Install the retained FWD cargo-compartment ceiling panel (Refer to AMM 25-51-11,

Page Block 401 and AMM 06-21-53, Page Block 001).

(b) Install the door actuator lining between FR22 and FR23.

(c) Install the retained AFT cargo-compartment ceiling panel (Refer to AMM 25-52-11,

Page Block 401 and AMM 06-21-53, Page Block 001).

(d) Install the door actuator lining between FR61 and F62.

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

REVISION No.: 02 - Apr 27/11 Page: 72

6

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

SERVICE BULLETIN

(e) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(f) Close the FWD cargo-compartment door 811 (Refer to AMM 52-30-00, Page Block

301).

(g) Close the AFT cargo-compartment door 812 (Refer to 52-30-00, Page Block 301).

(h) Remove the access platform(s).

**CONF 002

(1) Subtask 530389-942-201-001 - Close-up

Manpower Resources

Skills AIRFRAME

References

Aircraft Maintenance Manual (AMM) 06-21-53, Page Block 001

25-51-11, Page Block 401

25-52-11, Page Block 401

52-30-00, Page Block 301

(a) Install the retained FWD cargo-compartment ceiling panel (Refer to AMM 25-51-11,

Page Block 401 and AMM 06-21-53, Page Block 001).

(b) Install the door actuator lining between FR22 and FR23.

(c) Install the retained AFT cargo-compartment ceiling panel (Refer to AMM 25-52-11,

Page Block 401 and AMM 06-21-53, Page Block 001).

(d) Install the door actuator lining between FR61 and F62.

(e) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(f) Close the FWD cargo-compartment door 811 (Refer to AMM 52-30-00, Page Block

301).

(g) Close the AFT cargo-compartment door 812 (Refer to 52-30-00, Page Block 301).

(h) Remove the access platform(s).

**CONF 003

(1) Subtask 530389-942-201-001 - Close-up

Manpower Resources

Skills AIRFRAME

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

REVISION No.: 02 - Apr 27/11 Page: 73

6

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

SERVICE BULLETIN

References

Aircraft Maintenance Manual (AMM) 06-21-53, Page Block 001

25-51-11, Page Block 401

25-52-11, Page Block 401

52-30-00, Page Block 301

(a) Install the retained FWD cargo-compartment ceiling panel (Refer to AMM 25-51-11,

Page Block 401 and AMM 06-21-53, Page Block 001).

(b) Install the door actuator lining between FR22 and FR23.

(c) Install the retained AFT cargo-compartment ceiling panel (Refer to AMM 25-52-11,

Page Block 401 and AMM 06-21-53, Page Block 001).

(d) Install the door actuator lining between FR61 and F62.

(e) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(f) Close the FWD cargo-compartment door 811 (Refer to AMM 52-30-00, Page Block

301).

(g) Close the AFT cargo-compartment door 812 (Refer to 52-30-00, Page Block 301).

(h) Remove the access platform(s).

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

REVISION No.: 02 - Apr 27/11 Page: 74

6

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@A300

SERVICE BULLETIN

**CONF 001

SEAT TRACK 5

SEAT TRACK 3

SEAT TRACK 2

SEAT TRACK 4

Z130

A

FR21 FR22 FR23 FR24

B

C

SEAT TRACK 6

A_SB_530389_6_BAAA_01_02

FWD

A

Figure A-GBAAA - Sheet 01

Removal of the Existing Fasteners from the Crossbeam at FR22 and FR23

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

REVISION No.: 02 - Apr 27/11 Page: 75

6

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@A300

SERVICE BULLETIN

**CONF 001

D

FR22

(17)

E

FR23

A_SB_530389_6_BAAA_02_01

F

B

C

Figure A-GBAAA - Sheet 02

Removal of the Existing Fasteners from the Crossbeam at FR22 and FR23

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

REVISION No.: 02 - Apr 27/11 Page: 76

6

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@A300

SERVICE BULLETIN

**CONF 001

NOTE:

01 EXISTING FASTENER TO BE REMOVED

01 (7 POS)

01 (7 POS)

01

01 01 01

VIEW LOOKING FWD

VIEW LOOKING AFT

FR22

FR23

01 (6 POS)

01 (6 POS)

01

(17)

D

E

A_SB_530389_6_BAAA_03_02

Figure A-GBAAA - Sheet 03

Removal of the Existing Fasteners from the Crossbeam at FR22 and FR23

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

REVISION No.: 02 - Apr 27/11 Page: 77

6

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@A300

SERVICE BULLETIN

**CONF 001

IF PINS ARE INSTALLED, REMOVE THEM

(7 POS)

NOTE:

FR22

F

FWD

A_SB_530389_6_BAAA_04_00

02

02

Figure A-GBAAA - Sheet 04

Removal of the Existing Fasteners from the Crossbeam at FR22 and FR23

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

REVISION No.: 02 - Apr 27/11 Page: 78

6

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

SERVICE BULLETIN

**CONF 001

SEAT TRACK 6

SEAT TRACK 5

SEAT TRACK 3

SEAT TRACK 2

SEAT TRACK 4

FR21 FR22 FR23 FR24

B

C

A_SB_530389_6_BCAA_01_02

Z130

A

FWD

A

Figure A-GBCAA - Sheet 01

Installation of the Reinforcement at the Crossbeam at FR22 and FR23

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

REVISION No.: 02 - Apr 27/11 Page: 79

6

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

SERVICE BULLETIN

**CONF 001

D

FR22

E

FR23

2

1

3

A_SB_530389_6_BCAA_02_01

F

G

H

B

C

Figure A-GBCAA - Sheet 02

Installation of the Reinforcement at the Crossbeam at FR22 and FR23

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

REVISION No.: 02 - Apr 27/11 Page: 80

6

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

SERVICE BULLETIN

**CONF 001

01 HOLES TO BE INSPECTED IN ACCORDANCE WITH NTM 51−30−10

02 HOLES TO BE COLD EXPANDED IN ACCORDANCE WITH SRM 51−30−47

NOTE:

01

01

01

01

01

01 01

01

(6 POS)

(6 POS)

01

D

VIEW LOOKING FWD

FR22

VIEW LOOKING FWD

FR22

E

FOR RIVETS SYMBOLS, REFER TO SHEET 5

2

1

1.6mm

(0.06 in.)

02

02 02

POSITION OF SPLIT IN EXPANSION 

SLEEVE DURING COLD EXPANSION

A_SB_530389_6_BCAA_03_01

Figure A-GBCAA - Sheet 03

Installation of the Reinforcement at the Crossbeam at FR22 and FR23

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

REVISION No.: 02 - Apr 27/11 Page: 81

6

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

SERVICE BULLETIN

**CONF 001

VIEW LOOKING AFT

FR23

VIEW LOOKING AFT

FR23

FOR RIVETS SYMBOLS, REFER TO SHEET 5

01

01

01

01

01

3

(5 POS)

(5 POS)

01 HOLES TO BE INSPECTED IN ACCORDANCE WITH NTM 51−30−10

02 HOLES TO BE COLD EXPANDED IN ACCORDANCE WITH SRM 51−30−47

NOTE:

A

B

DIMENSIONS

mm (in.)

A 40.0 1.57

B 49.0 1.93

F

G

POSITION OF SPLIT IN EXPANSION 

SLEEVE DURING COLD EXPANSION

02 02 02

A_SB_530389_6_BCAA_04_02

Figure A-GBCAA - Sheet 04

Installation of the Reinforcement at the Crossbeam at FR22 and FR23

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

REVISION No.: 02 - Apr 27/11 Page: 82

6

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

SERVICE BULLETIN

**CONF 001

HOLE

SYMBOL ITEM

EN6115K3−3 PIN

P/N DESCRIPTION KIT REMARKS

6

4 ASNA2528−3 COLLAR

EN6115K3−4 PIN

ASNA2528−3 COLLAR

EN6115K3−5 PIN

ASNA2528−3 COLLAR

EN6115K3X4 PIN

ASNA2528−3 COLLAR

EN6115K3X5 PIN

ASNA2528−3 COLLAR

EN6115K3AX4 PIN

ASNA2528−3A COLLAR

EN6115K3AX5 PIN

ASNA2528−3A COLLAR

8

4

9

4

10

4

11

5

12

5

EN6115K3AX6 PIN

ASNA2528−3A COLLAR

EN6115K3A6 PIN

ASNA2528−3A COLLAR

DAN5−6−4X PIN

DAN11−6X COLLAR

13

5

14

5

15

16

D02

D02

D02

D02

D02

D02

D02

D02

D02

D02

STDN

4−4−N

4−4−N

6−2−N

6−2−N

6−2−N

STARTING HOLE DIAMETER

MIN. MAX.

4.29 mm

(0.169 in)

4.34 mm

(0.171 in)

4.29 mm

(0.169 in)

4.34 mm

(0.171 in)

5.31 mm

(0.209 in)

5.38 mm

(0.212 in)

5.31 mm

(0.209 in)

5.38 mm

(0.212 in)

5.31 mm

(0.209 in)

5.38 mm

(0.212 in)

FINAL HOLE DIAMETER

MIN. MAX.

4.72 mm

(0.185 in)

4.76 mm

(0.187 in)

4.72 mm

(0.185 in)

4.76 mm

(0.187 in)

5.85 mm

(0.230 in)

5.89 mm

(0.231 in)

5.85 mm

(0.230 in)

5.89 mm

(0.231 in)

5.85 mm

(0.230 in)

5.89 mm

(0.231 in)

5.85 mm

(0.230 in)

5.89 mm

(0.231 in)

5.06 mm

(0.199 in)

5.09 mm

(0.20 in)

5.06 mm

(0.199 in)

5.09 mm

(0.20 in)

5.45 mm

(0.215 in)

5.49 mm

(0.216 in)

HOLES TO BE COLD EXPANDED IN ACCORDANCE WITH SRM 51−30−47 A_SB_530389_6_BCAA_05_02 02

NOTE:

STDN = STANDARD TOOL DIAMETER NUMBER

EN6115K3−3 PIN

ASNA2528−3 COLLAR

D02 4.72 mm

(0.185 in)

4.76 mm

(0.187 in)

EN6115K3−4 PIN

ASNA2528−3 COLLAR

7

4

D02 4.72 mm

(0.185 in)

4.76 mm

(0.187 in)

02

02

02

02

02

DAN5−6−6X PIN

DAN11−6X COLLAR

5.11mm

(0.201 in.)

5.15mm

(0.203 in.)

D02

55

6

4

7

4

16

Figure A-GBCAA - Sheet 05

Installation of the Reinforcement at the Crossbeam at FR22 and FR23

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

REVISION No.: 02 - Apr 27/11 Page: 83

6

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

SERVICE BULLETIN

**CONF 001

FOR RIVET SYMBOLS, REFER TO SHEET 5

(7 POS) 03

03 IF PINS HAVE BEEN REMOVED, INSTALL NEW PINS

NOTE:

FR22

FWD

A_SB_530389_6_BCAA_06_00

H

Figure A-GBCAA - Sheet 06

Installation of the Reinforcement at the Crossbeam at FR22 and FR23

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

REVISION No.: 02 - Apr 27/11 Page: 84

6

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

SERVICE BULLETIN

**CONF 002

SEAT TRACK 6

SEAT TRACK 5

SEAT TRACK 3

SEAT TRACK 2

SEAT TRACK 4

Z130

A

FR21 FR22 FR23 FR24

B

C

A_SB_530389_6_BEAA_01_02

FWD

A

Figure A-GBEAA - Sheet 01

Removal of the Existing Fasteners from the Crossbeam at FR22 and FR23

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

REVISION No.: 02 - Apr 27/11 Page: 85

6

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

SERVICE BULLETIN

**CONF 002

D

FR22

E C

B

FR23

A_SB_530389_6_BEAA_02_01

F

Figure A-GBEAA - Sheet 02

Removal of the Existing Fasteners from the Crossbeam at FR22 and FR23

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

REVISION No.: 02 - Apr 27/11 Page: 86

6

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@A300

SERVICE BULLETIN

**CONF 002

NOTE:

01 (7 POS)

01 (7 POS)

01

01

VIEW LOOKING FWD

VIEW LOOKING AFT

FR22

FR23

01 (6 POS)

01 (6 POS)

D

E

A_SB_530389_6_BEAA_03_02 01 EXISTING FASTENER TO BE REMOVED

Figure A-GBEAA - Sheet 03

Removal of the Existing Fasteners from the Crossbeam at FR22 and FR23

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

REVISION No.: 02 - Apr 27/11 Page: 87

6

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

SERVICE BULLETIN

**CONF 002

IF PINS ARE INSTALLED, REMOVE THEM

(7 POS)

NOTE:

FR22

FWD

02

02 A_SB_530389_6_BEAA_04_00

F

Figure A-GBEAA - Sheet 04

Removal of the Existing Fasteners from the Crossbeam at FR22 and FR23

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

REVISION No.: 02 - Apr 27/11 Page: 88

6

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

SERVICE BULLETIN

**CONF 002

SEAT TRACK 6

SEAT TRACK 5

SEAT TRACK 3

SEAT TRACK 2

SEAT TRACK 4

Z130

A

FR21 FR22 FR23 FR24

B

C

A_SB_530389_6_BGAA_01_02

FWD

A

Figure A-GBGAA - Sheet 01

Installation of the Reinforcement at the Crossbeam at FR22 and FR23

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

REVISION No.: 02 - Apr 27/11 Page: 89

6

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

SERVICE BULLETIN

**CONF 002

FR22

FR23

21

20

H

D E

F G

J K

B

C

L M

A_SB_530389_6_BGAA_02_03

Figure A-GBGAA - Sheet 02

Installation of the Reinforcement at the Crossbeam at FR22 and FR23

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

REVISION No.: 02 - Apr 27/11 Page: 90

6

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

SERVICE BULLETIN

**CONF 002

VIEW LOOKING FWD

FR22

VIEW LOOKING FWD

FR22

01

01

(6 POS)

01 01 (6 POS)

01

A

FOR RIVETS SYMBOLS, REFER TO SHEET 5

FOR DIMENSION, REFER TO SHEET 5

20

D

E

C

01 HOLES TO BE INSPECTED IN ACCORDANCE WITH NTM 51−30−10

02 HOLES TO BE COLD EXPANDED IN ACCORDANCE WITH SRM 51−30−47

NOTE:

POSITION OF SPLIT IN EXPANSION 

SLEEVE DURING COLD EXPANSION

02

02

A_SB_530389_6_BGAA_03_03

Figure A-GBGAA - Sheet 03

Installation of the Reinforcement at the Crossbeam at FR22 and FR23

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

REVISION No.: 02 - Apr 27/11 Page: 91

6

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

SERVICE BULLETIN

**CONF 002

FOR RIVETS SYMBOLS, REFER TO SHEET 5

FOR DIMENSION, REFER TO SHEET 5

VIEW LOOKING AFT

FR23

VIEW LOOKING AFT

FR23

G

01

01

01 (5 POS)

(5 POS) F

21

F

H

01 HOLES TO BE INSPECTED IN ACCORDANCE WITH NTM 51−30−10

02 HOLES TO BE COLD EXPANDED IN ACCORDANCE WITH SRM 51−30−47

NOTE:

POSITION OF SPLIT IN EXPANSION 

SLEEVE DURING COLD EXPANSION

02 02

A_SB_530389_6_BGAA_04_02

Figure A-GBGAA - Sheet 04

Installation of the Reinforcement at the Crossbeam at FR22 and FR23

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

REVISION No.: 02 - Apr 27/11 Page: 92

6

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

SERVICE BULLETIN

**CONF 002

HOLE

SYMBOL ITEM

EN6115K3−3 PIN

P/N DESCRIPTION KIT

6

4 ASNA2528−3 COLLAR

DIMENSIONS

mm (in.)

A 1.8 0.07

B 4.0 0.16

EN6115K3X4 PIN

ASNA2528−3 COLLAR

9

4

EN6115K3X5 PIN

ASNA2528−3 COLLAR

10

4

EN6115K3AX5 PIN

ASNA2528−3A COLLAR

12

5

EN6115K3AX6 PIN

ASNA2528−3A COLLAR

EN6115K3A6 PIN

ASNA2528−3A COLLAR

D03

D03

D03

D03

D03

D03

STDN REMARKS

STARTING HOLE DIAMETER

MIN. MAX.

FINAL HOLE DIAMETER

MIN. MAX.

4.72 mm

(0.185 in)

4.76 mm

(0.187 in)

4.72 mm

(0.185 in)

4.76 mm

(0.187 in)

5.06 mm

(0.199 in)

5.09 mm

(0.20 in)

6−2−N

6−2−N

5.31 mm

(0.209 in)

5.38 mm

(0.212 in)

5.31 mm

(0.209 in)

5.38 mm

(0.212 in)

5.85 mm

(0.230 in)

5.89 mm

(0.231 in)

5.45 mm

(0.215 in)

5.49 mm

(0.216 in)

STDN = STANDARD TOOL DIAMETER NUMBER

DAN5−6−6X

COLLAR

PIN

DAN11−6X

D03 5.11 mm

(0.201 in)

5.15 mm

(0.203 in)

HOLES TO BE COLD EXPANDED IN ACCORDANCE WITH SRM 51−30−47

NOTE:

55

02

EN6115K3AX6 PIN

ASNA2528−3A COLLAR

D03

5.85 mm

(0.230 in)

5.89 mm

(0.231 in)

EN6115K3−3 PIN

ASNA2528−3 COLLAR

D03 4−4−N 4.29 mm

(0.169 in)

4.34 mm

(0.171 in) 02

02

02

4

6

13

5

13

5

14

5

16

4.72 mm

(0.185 in)

4.76 mm

(0.187 in)

5.85 mm

(0.230 in)

5.89 mm

(0.231 in)

C 7.5 0.30

D R 8.0 0.31

E 38.1 1.50

F 40.0 1.57

G 45.0 1.77

H 54.0 2.13

J 33.0 1.30

K 41.0 1.61

A_SB_530389_6_BGAA_05_04

Figure A-GBGAA - Sheet 05

Installation of the Reinforcement at the Crossbeam at FR22 and FR23

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

REVISION No.: 02 - Apr 27/11 Page: 93

6

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

SERVICE BULLETIN

**CONF 002

FOR RIVET SYMBOLS, REFER TO SHEET 5

(7 POS) 03

03 IF PINS HAVE BEEN REMOVED, INSTALL NEW PINS

NOTE:

FR22

FWD

A_SB_530389_6_BGAA_06_00

H

Figure A-GBGAA - Sheet 06

Installation of the Reinforcement at the Crossbeam at FR22 and FR23

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

REVISION No.: 02 - Apr 27/11 Page: 94

6

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

SERVICE BULLETIN

**CONF 002

05 REWORK THE REINFORCEMENT, ITEM 20, TO THE NEW CONTOUR

IN ACCORDANCE WITH SRM 51−27−11

D

B

E

G

D

D

FOR DIMENSIONS, REFER TO SHEET 5

05

04

04 REINFORCEMENT, ITEM 20, WITH OLD CONTOUR

NOTE:

J

K

A_SB_530389_6_BGAA_07_00

20

20

Figure A-GBGAA - Sheet 07

Installation of the Reinforcement at the Crossbeam at FR22 and FR23

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

REVISION No.: 02 - Apr 27/11 Page: 95

6

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@A300

SERVICE BULLETIN

**CONF 002

05 REWORK THE REINFORCEMENT, ITEM 20, TO THE NEW CONTOUR

IN ACCORDANCE WITH SRM 51−27−11

D

B

E

G

D

D

FOR DIMENSIONS, REFER TO SHEET 5

04

04 REINFORCEMENT, ITEM 20, WITH OLD CONTOUR

NOTE:

20

L

M

D

B

J

K

D

D

05 20

A_SB_530389_6_BGAA_08_00

Figure A-GBGAA - Sheet 08

Installation of the Reinforcement at the Crossbeam at FR22 and FR23

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

REVISION No.: 02 - Apr 27/11 Page: 96

6

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@A300

SERVICE BULLETIN

**CONF 003

SEAT TRACK 6

SEAT TRACK 5

SEAT TRACK 3

SEAT TRACK 2

SEAT TRACK 4

Z130

A

FR21 FR22 FR23 FR24

B

E

A_SB_530389_6_BJAA_01_02

FWD

A

Figure A-GBJAA - Sheet 01

Removal of the Existing Fasteners from the Crossbeam at FR22 and FR23

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

REVISION No.: 02 - Apr 27/11 Page: 97

6

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@A300

SERVICE BULLETIN

**CONF 003

FR22

(26)

(26)

(28)

(27)

(25)

D

C

B

A_SB_530389_6_BJAA_02_01

G

Figure A-GBJAA - Sheet 02

Removal of the Existing Fasteners from the Crossbeam at FR22 and FR23

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

REVISION No.: 02 - Apr 27/11 Page: 98

6

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@A300

SERVICE BULLETIN

**CONF 003

A A

D

E

E

H

G

F

B

A C

DIMENSIONS

mm (in.)

A 1.8 0.07

B 2.3 0.09

C R 4.0 0.16

D 5.0 0.20

A A

DIMENSIONS

mm (in.)

E R 8.0 0.31

F 66.5 2.62

G 91.8 TO 92.2 3.61 TO 3.63

H 94.1 3.70

REWORKED AREA

C

A_SB_530389_6_BJAA_03_01

−Y1959

Figure A-GBJAA - Sheet 03

Removal of the Existing Fasteners from the Crossbeam at FR22 and FR23

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

REVISION No.: 02 - Apr 27/11 Page: 99

6

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@A300

SERVICE BULLETIN

**CONF 003

FR23

NOTE:

(8 POS)

01 (8 POS)

01

01

01

01

01

01 (4 POS)

01

01

(28)

(25)

(26) (26) (27)

01 01

01

VIEW LOOKING AFT

FR23

01 (6 POS)

01 (6 POS)

VIEW LOOKING FWD

FR22

E F F

D 01

A_SB_530389_6_BJAA_04_02 01 EXISTING FASTENER TO BE REMOVED

Figure A-GBJAA - Sheet 04

Removal of the Existing Fasteners from the Crossbeam at FR22 and FR23

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

REVISION No.: 02 - Apr 27/11 Page: 100

6

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

SERVICE BULLETIN

**CONF 003

IF PINS ARE INSTALLED, REMOVE THEM

(7 POS)

NOTE:

FR22

FWD

02

02 A_SB_530389_6_BJAA_05_00

G

Figure A-GBJAA - Sheet 05

Removal of the Existing Fasteners from the Crossbeam at FR22 and FR23

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

REVISION No.: 02 - Apr 27/11 Page: 101

6

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

SERVICE BULLETIN

**CONF 003

SEAT TRACK 6

SEAT TRACK 5

SEAT TRACK 3

SEAT TRACK 2

SEAT TRACK 4

Z130

A

FR21 FR22 FR23 FR24

B

E

A_SB_530389_6_BLAA_01_02

FWD

A

Figure A-GBLAA - Sheet 01

Installation of the Reinforcement at the Crossbeam at FR22 and FR23

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

REVISION No.: 02 - Apr 27/11 Page: 102

6

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

SERVICE BULLETIN

**CONF 003

FR22

22

(26)

(26)

(28)

(27)

25

23

23

C D

B

A_SB_530389_6_BLAA_02_01

H

Figure A-GBLAA - Sheet 02

Installation of the Reinforcement at the Crossbeam at FR22 and FR23

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

REVISION No.: 02 - Apr 27/11 Page: 103

6

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

SERVICE BULLETIN

**CONF 003

(28)

(26)

(26)

(27)

VIEW LOOKING FWD

FR22

01 HOLES TO BE INSPECTED IN ACCORDANCE WITH NTM 51−30−10

02 HOLES TO BE COLD EXPANDED IN ACCORDANCE WITH SRM 51−30−47

NOTE:

FOR DIMENSION, REFER TO SHEET 5

VIEW LOOKING FWD

FR22

01 01

01 01

(6 POS)

(6 POS)

01

01

01

01 01

01 (4 POS)

01

01

01

01

01

22

D

A A

A

F

D

K

B

J

23

A A

FOR RIVETS SYMBOLS, REFER TO SHEET 5

C

A

A

25

25

E

01

POSITION OF SPLIT IN EXPANSION 

SLEEVE DURING COLD EXPANSION

02

02

02

02

A_SB_530389_6_BLAA_03_01

Figure A-GBLAA - Sheet 03

Installation of the Reinforcement at the Crossbeam at FR22 and FR23

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

REVISION No.: 02 - Apr 27/11 Page: 104

6

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

SERVICE BULLETIN

**CONF 003

FR23

VIEW LOOKING AFT

FR23

E F F

VIEW LOOKING AFT

FR23

G

G

01 HOLES TO BE INSPECTED IN ACCORDANCE WITH NTM 51−30−10

02 HOLES TO BE COLD EXPANDED IN ACCORDANCE WITH SRM 51−30−47

NOTE:

FOR DIMENSION, REFER TO SHEET 5

FOR RIVETS SYMBOLS, REFER TO SHEET 5

G

C

H

01

01

01

01

(5 POS)

(5 POS)

POSITION OF SPLIT IN EXPANSION 

SLEEVE DURING COLD EXPANSION

02

02

A_SB_530389_6_BLAA_04_01

Figure A-GBLAA - Sheet 04

Installation of the Reinforcement at the Crossbeam at FR22 and FR23

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

REVISION No.: 02 - Apr 27/11 Page: 105

6

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

SERVICE BULLETIN

**CONF 003

HOLE

SYMBOL ITEM

EN6115K3−5 PIN

P/N DESCRIPTION KIT

4 ASNA2528−3 COLLAR

DIMENSIONS

mm (in.)

A 5.0 0.20

B DIA 8.0 DIA 0.31

C 10.0 0.39

D 11.0 0.43

PIN

COLLAR

EN6115K3X5

PIN

ASNA2528−3

COLLAR

10

4

EN6115K3X6 PIN

COLLAR

EN6115K3X7 PIN

COLLAR

EN6115K3AX7 PIN

5 ASNA2528−3A COLLAR

8

EN6115K3AX6

ASNA2528−3A

13

5

30

4 ASNA2528−3

31

32

ASNA2528−3

35

36

37

38

RIVET

RIVET

RIVET

RIVET

EN6081D3−06

EN6081D4−07

EN6081D5−07

EN6081D6−09

E 11.6 0.46

F

G 22.0 0.87

H 25.0 0.98

J 27.6 1.09

4

K 50.0 1.97

21.5 0.85

D04

D04

D04

D04

D04

D04

D04

D04

D04

D04

STDN = STANDARD TOOL DIAMETER NUMBER

STDN REMARKS

4−4−N

STARTING HOLE DIAMETER

MIN. MAX.

4.29 mm

(0.169 in)

4.34 mm

(0.171 in)

FINAL HOLE DIAMETER

MIN. MAX.

4.72 mm

(0.185 in)

4.76 mm

(0.187 in)

5.06 mm

(0.199 in)

5.09 mm

(0.20 in)

5.85 mm

(0.230 in)

5.89 mm

(0.231 in)

5.06 mm

(0.199 in)

5.09 mm

(0.20 in)

5.06 mm

(0.199 in)

5.09 mm

(0.20 in)

5.31 mm

(0.209 in)

5.38 mm

(0.212 in)

5.85 mm

(0.230 in)

5.89 mm

(0.231 in) 6−2−N

A_SB_530389_6_BLAA_05_03

DAN5−6−6X

COLLAR

PIN

DAN11−6X

D04 5.11 mm

(0.201 in)

5.15 mm

(0.203 in)

HOLES TO BE COLD EXPANDED IN ACCORDANCE WITH SRM 51−30−47

NOTE:

55

5.31 mm

(0.209 in)

5.38 mm

(0.212 in) 6−2−N

02

02

02

02

16

Figure A-GBLAA - Sheet 05

Installation of the Reinforcement at the Crossbeam at FR22 and FR23

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

REVISION No.: 02 - Apr 27/11 Page: 106

6

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

SERVICE BULLETIN

**CONF 003

(7 POS)

FR22

FWD

A_SB_530389_6_BLAA_06_00

H

03

FOR RIVET SYMBOLS, REFER TO SHEET 5

03 IF PINS HAVE BEEN REMOVED, INSTALL NEW PINS

NOTE:

Figure A-GBLAA - Sheet 06

Installation of the Reinforcement at the Crossbeam at FR22 and FR23

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

REVISION No.: 02 - Apr 27/11 Page: 107

6

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

SERVICE BULLETIN

**CONF ALL

SEAT TRACK 5

SEAT TRACK 3

SEAT TRACK 2

SEAT TRACK 4

A

B

C

SEAT TRACK 6

FR60 FR61 FR62 FR63

Z150

A_SB_530389_6_BNAA_01_02

FWD

A

Figure A-GBNAA - Sheet 01

Removal of the Existing Rivets from the Crossbeam at FR61 and FR62

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

REVISION No.: 02 - Apr 27/11 Page: 108

6

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

SERVICE BULLETIN

**CONF ALL

D

FR61

FR62

E

(43)

(44)

C

(45)

A_SB_530389_6_BNAA_02_01

F

B

Figure A-GBNAA - Sheet 02

Removal of the Existing Rivets from the Crossbeam at FR61 and FR62

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

REVISION No.: 02 - Apr 27/11 Page: 109

6

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

SERVICE BULLETIN

**CONF ALL

NOTE:

01 (7 POS)

01 01

VIEW LOOKING FWD

VIEW LOOKING AFT

FR61

FR62

01 (7 POS)

01 (6 POS)

(6 POS)

01

(43)

(44)

(45)

E

D

01

A_SB_530389_6_BNAA_03_02 01 EXISTING FASTENER TO BE REMOVED

Figure A-GBNAA - Sheet 03

Removal of the Existing Rivets from the Crossbeam at FR61 and FR62

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

REVISION No.: 02 - Apr 27/11 Page: 110

6

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

SERVICE BULLETIN

**CONF ALL

IF PINS ARE INSTALLED, REMOVE THEM

(7 POS)

NOTE:

FR61

F

FWD

A_SB_530389_6_BNAA_04_00

02

02

Figure A-GBNAA - Sheet 04

Removal of the Existing Rivets from the Crossbeam at FR61 and FR62

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

REVISION No.: 02 - Apr 27/11 Page: 111

6

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

SERVICE BULLETIN

**CONF ALL

SEAT TRACK 5

SEAT TRACK 3

SEAT TRACK 2

SEAT TRACK 4

A

B

C

SEAT TRACK 6

FR60 FR61 FR62 FR63

Z150

A_SB_530389_6_BPAA_01_02

FWD

A

Figure A-GBPAA - Sheet 01

Installation of the Reinforcement at the Crossbeam at FR61 and FR62

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

REVISION No.: 02 - Apr 27/11 Page: 112

6

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@A300

SERVICE BULLETIN

**CONF ALL

D

FR61

E

40

FR62

F

G

41

43

42

45

44

NOTE:

01 DRILL THE HOLE TO DIA. 6.5mm (0.25 in.) FOR INSTALLATION OF THE

01

B

NUTE−PLATE, ITEM 44, DURING THE INSTALLATION OF THE CEILING PANEL

C

A_SB_530389_6_BPAA_02_01

H

Figure A-GBPAA - Sheet 02

Installation of the Reinforcement at the Crossbeam at FR61 and FR62

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

REVISION No.: 02 - Apr 27/11 Page: 113

6

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

SERVICE BULLETIN

**CONF ALL

VIEW LOOKING FWD

FR61

VIEW LOOKING FWD

FR61

FOR RIVETS SYMBOLS, REFER TO SHEET 5

02

02

(6 POS)

02 (6 POS)

02

D

02 02

C

FOR DIMENSION, REFER TO SHEET 5

40

02 HOLES TO BE INSPECTED IN ACCORDANCE WITH NTM 51−30−10

03 HOLES TO BE COLD EXPANDED IN ACCORDANCE WITH SRM 51−30−47

NOTE:

POSITION OF SPLIT IN EXPANSION 

SLEEVE DURING COLD EXPANSION

E

03

02

03

A_SB_530389_6_BPAA_03_01

Figure A-GBPAA - Sheet 03

Installation of the Reinforcement at the Crossbeam at FR61 and FR62

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

REVISION No.: 02 - Apr 27/11 Page: 114

6

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

SERVICE BULLETIN

**CONF ALL

FOR RIVET SYMBOLS, REFER TO SHEET 5

FOR DIMENSION, REFER TO SHEET 5

VIEW LOOKING AFT

FR62

04 HOLES CLOSED, ONLY IN THE CROSSBEAM

04

02

(5 POS)

(5 POS)

02 02 02

A

B

A

A

41

43

42

VIEW LOOKING AFT

FR62

45

50

02 HOLES TO BE INSPECTED IN ACCORDANCE WITH NTM 51−30−10

03 HOLES TO BE COLD EXPANDED IN ACCORDANCE WITH SRM 51−30−47

NOTE:

F

G

POSITION OF SPLIT IN EXPANSION 

SLEEVE DURING COLD EXPANSION

03

03

02

(2 POS)

44

A_SB_530389_6_BPAA_04_03

A A

Figure A-GBPAA - Sheet 04

Installation of the Reinforcement at the Crossbeam at FR61 and FR62

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

REVISION No.: 02 - Apr 27/11 Page: 115

6

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

SERVICE BULLETIN

**CONF ALL

HOLE

SYMBOL ITEM

EN6115K3−3 PIN

P/N DESCRIPTION KIT

6

4 ASNA2528−3 COLLAR

DIMENSIONS

mm (in)

A 8.1 0.32

B 9.5 0.37

C 20.0 0.79

D01

STDN REMARKS

STARTING HOLE DIAMETER

MIN. MAX.

FINAL HOLE DIAMETER

MIN. MAX.

4.72 mm

(0.185 in)

4.76 mm

(0.187 in)

EN6115K3X5 PIN

ASNA2528−3 COLLAR

EN6115K3AX5 PIN

ASNA2528−3A COLLAR

10

4

12

5

36

38

50

51

5

52

5

53

RIVET

RIVET

RIVET

RIVET

EN6081D4−07

EN6081D6−09

EN6069AD3−05

EN6069AD4−05

EN6115K3A5

COLLAR

PIN

EN6115K3AX3

ASNA2528−3A

ASNA2528−3A

D01

D01

D01

D01

D01

D01

D01

D01

6−2−N 5.31 mm

(0.209 in)

5.38 mm

(0.212 in)

5.85 mm

(0.230 in)

5.89 mm

(0.231 in)

5.06 mm

(0.199 in)

5.09 mm

(0.20 in)

STDN = STANDARD TOOL DIAMETER NUMBER

5.45 mm

(0.215 in)

5.49 mm

(0.216 in)

5.85 mm

(0.230 in)

5.89 mm

COLLAR (0.231 in)

PIN

EN6115K3−3 PIN

ASNA2528−3 COLLAR

D01 4−4−N 4.29 mm

(0.169 in)

4.34 mm

(0.171 in)

DAN5−6−6X

COLLAR

PIN

DAN11−6X

D01 5.11 mm

(0.201 in)

5.15 mm

(0.203 in)

DAN5−6−6Y

COLLAR

PIN

DAN11−6Y

D01 5.51 mm

(0.217 in)

5.55 mm

(0.218 in)

HOLES TO BE COLD EXPANDED IN ACCORDANCE WITH SRM 51−30−47

NOTE:

03

03

03

55

A_SB_530389_6_BPAA_05_03

6

4

16

56

57

4.72 mm

(0.185 in)

4.76 mm

(0.187 in)

Figure A-GBPAA - Sheet 05

Installation of the Reinforcement at the Crossbeam at FR61 and FR62

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

REVISION No.: 02 - Apr 27/11 Page: 116

6

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

SERVICE BULLETIN

**CONF ALL

(7 POS)

FR61

FWD

A_SB_530389_6_BPAA_06_00 FOR RIVET SYMBOLS, REFER TO SHEET 5

IF REQUIRED, INSTALL 2ND OVERSIZE PINS

IF PINS HAVE BEEN REMOVED, INSTALL NEW PINS

NOTE:

04

05

04

05

H

Figure A-GBPAA - Sheet 06

Installation of the Reinforcement at the Crossbeam at FR61 and FR62

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

REVISION No.: 02 - Apr 27/11 Page: 117

6

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@A300

SERVICE BULLETIN

REPORTING SHEET

TITLE: FUSELAGE - GENERAL - REINFORCE THE FLOOR CROSSBEAMS AT

FR22/FR23 AND FR61/FR62

MODIFICATION No.: 13434D23217

Please complete the appropriate item (A or B):

A - SB WILL BE embodied YES/NO (if NO please comment)

If YES, aircraft concerned (as per SB effectivity by default) and planned dates (month/year) of

embodiment:

B - SB HAS BEEN embodied on aircraft:

Operator comments:

From Airline:

Name/Title:

Signature: Date:

If operational documentation is affected (see Paragraph 1.K of this SB): If information is needed prior to

next normal revision or prior to SB embodiment, please indicate required service(s):

Either: Modification Operational Impact (MOI), if available YES/NO

Or : Intermediate revision YES/NO

Important Information: This SB will only be incorporated in your maintenance and operational

documentation if this sheet is returned to Airbus and signed by a duly authorised representative. With

the next feasible revision, this will result in

- Updating of maintenance documentation to show pre and post SB data.

- Updating of maintenance and operational documentation to show post SB data after embodiment.

If this SB requires previous or simultaneous accomplishment of other SBs, Airbus shall automatically

include them in the manual revisions. Refer to SIL 00-037 for detailed information.

Please return this completed sheet to:

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX FRANCE

Attn: SDC32 Technical Data and Documentation Services

FAX: (+33) 5 61 93 28 06

e-mail: sb.reporting@airbus.com

or via your Resident Customer Support Office.

Alternatively, SB lists via letters or fax are also accepted.

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

REVISION No.: 02 - Apr 27/11 Page: 1

6

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@A300

SERVICE BULLETIN

QUALITY PERCEPTION FORM

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

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

improve the quality of our Service Bulletins.

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

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

- Quality rating of this SB 4 3 2 1

- Quality rating of the Accomplishment Instructions 4 3 2 1

- Quality rating of the Illustrations 4 3 2 1

- Is this SB easy to understand ? Y / N

If you have had difficulties in the accomplishment of this SB please quote below the area(s) and give a

short description of the issue.

Planning Material Instructions

X Effectivity X Kit content X Preparation

X Reason X List of Materials Operator Supplied X Mod/Inspection

X Manpower X Industry support X Test

X References X Re-identification X Close-Up

X Publication X Tooling X Illustrations

Comments:

Operator: Date:

Name/Title:

Please return this form to:

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX FRANCE

Attn : SEM4 Service Bulletins Management

FAX : (33) 5 61 93 42 51

Or via your Resident Customer Support Office.

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389

REVISION No.: 02 - Apr 27/11 Page: 1

6

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