@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.

MANDATORY MANDATORY MANDATORY

ATA SYSTEM: 53

TITLE: FUSELAGE - STRUCTURE - INSPECT FOR CROSSBEAM AT

JUNCTION WITH LOWER DECK CARGO DOOR ACTUATOR BEAM AT

FR22/23 AND FR61/FR62

**CONF ALL

MODIFICATIONS

None

REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

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

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

laboratory analysis revealed that the cracks are initiated in the fastener hole propagating vertically. The

design of FWD and AFT cargo door attachments are similar to the crossbeams at FR22/23 and

FR61/FR62 and should be inspected.

On passenger aircraft, in case of cracks being present in a crossbeam (upper and lower web), the floor

grid cannot withstand ultimate load condition. On freighter aircraft this is not the case due to different

load distribution via the pallets.

This Service Bulletin details the inspection procedure for aircraft on which the crossbeams are not

previously repaired by the Structure Repair Manual (SRM) or a Repair Approval Sheet (RAS).

This inspection procedure details :

- High Frequency Eddy Current inspection which will inspect the crossbeams for cracks at FR22/23

and FR61/62 on passenger aircraft,

- High Frequency Eddy Current and a Ultra Sonic inspection which will inspect the crossbeam for

crack(s) at FR22/23 on freighter aircraft,

- High Frequency Eddy Current inspection which will inspect the crossbeam for cracks at FR61/62

on freighter aircraft,

before the accumulation of 10000 total aircraft flight cycles.

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0390

REVISION No.: 00 - Jan 15/10 Page: 1

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SERVICE BULLETIN

SUMMARY

NOTE: For aircraft on which the crossbeams have been previously repaired by the Structure

Repair Manual (SRM) or a Repair Approval Sheet (RAS) the operator has to contact

AIRBUS before reaching the threshold or the grace period for further instructions.

In the case no crack(s) are found :

- repeat this inspection at an interval not to exceed 600 Flight Cycles (FC)

or

- accomplish the Modification Service Bulletin A300-53-0389 within 600 Flight Cycles (FC) after the

last inspection in accordance with this Inspection Service Bulletin.

. The accomplishment of Modification Service Bulletin No. A300-53-0389 cancels the

requirements of this Inspection Service Bulletin.

In the case crack(s) are found :

- longer than 7.0mm 0.27in.) contact AIRBUS before the next flight and follow their instructions.

- smaller than or equal to 7.0mm 0.27in.) contact AIRBUS before the next flight and follow their

instructions within :

. 10FC, if crack(s) were detected by Ultra Sonic inspection procedure,

. 50FC, if crack(s) were detected by a High Frequency Eddy Current inspection procedure.

The accomplishment of this Service Bulletin :

- monitors the structure surrounding the rivet heads on crossbeams at FR22/23 and FR61/62

- can prevent heavy repair.

The accomplishment of Modification Service Bulletin No. A300-53-0389 cancels the requirements of this

Inspection Service Bulletin.

NOTE: This Service Bulletin is mandatory for all passenger aircraft, recommended for freighter

aircraft.

NOTE: If operators have previously accomplished the Modification Service Bulletin No.

A300-53-0389, the accomplishment of this Inspection Service Bulletin is no longer

required.

GENERAL EVALUATION

EVALUATION TABLE

COMPLIANCE MANDATORY CANCELS INSPECTION SB NO

POTENTIAL AD YES A/C OPERATION AFFECTED NO

RELIABILITY AFFECTED NO PAX COMFORT AFFECTED NO

COST SAVING NO ETOPS AFFECTED NO

STRUCTURAL LIFE EXTN NO VENDOR SB INVOLVED NO

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SERVICE BULLETIN

SUMMARY

MATERIAL PRICE INFORMATION

**CONF 001

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

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

Compartment Doors

**CONF 002

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

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

Compartment Doors

EFFECTIVITY

**CONF ALL

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

50W 72U AFG BCS DHL F2I FLM IAW IRA IRB IRM KZU MIX

MNB MSR NTR RUN SOP TDX TNO TSY

CONCURRENT REQUIREMENTS

None

REFERENCES / REPERCUSSIONS

TFU None

OEB None

AOT None

SIL None

LINE MAINTENANCE AFFECTED No

LIFE LIMIT None

OTHER None

NATURE OF THE WORK

AIRCRAFT YES

EQUIPMENT NO

HARD NO

SOFT NO

OBRM NO

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SERVICE BULLETIN

SUMMARY

MANPOWER

**CONF 001

Task 530390-832-848-001: Inspection

TOTAL MANHOURS 7.50

ELAPSED TIME (HOURS) 4.00

**CONF 002

Task 530390-832-848-001: Inspection

TOTAL MANHOURS 7.50

ELAPSED TIME (HOURS) 4.00

APPENDICES

**CONF ALL

None

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0390

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SERVICE BULLETIN

SUMMARY

**CONF 001

SEAT TRACK 5

SEAT TRACK 3

SEAT TRACK 2

SEAT TRACK 4

FR21 FR22 FR23 FR24

SEAT TRACK 6

HFEC INSPECTION AREA

FWD

A

A_SB_530390_6_SAAA_01_00

Z130

A

Figure A-GSAAA - Sheet 01

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SERVICE BULLETIN

SUMMARY

**CONF 001

SEAT TRACK 5

SEAT TRACK 3

SEAT TRACK 2

SEAT TRACK 4

SEAT TRACK 6

HFEC INSPECTION AREA

FWD

A

A_SB_530390_6_SAAA_02_00

FR60 FR61 FR62 FR63

A

Z150

Figure A-GSAAA - Sheet 02

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0390

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SERVICE BULLETIN

SUMMARY

**CONF 002

SEAT TRACK 5

SEAT TRACK 3

SEAT TRACK 2

SEAT TRACK 4

FR21 FR22 FR23 FR24

SEAT TRACK 6

HFEC INSPECTION

FWD

A

Z130

A

A_SB_530390_6_SBAA_01_00

AREA

US INSPECTION

AREA

Figure A-GSBAA - Sheet 01

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0390

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SERVICE BULLETIN

SUMMARY

**CONF 002

SEAT TRACK 5

SEAT TRACK 3

SEAT TRACK 2

SEAT TRACK 4

SEAT TRACK 6

HFEC INSPECTION AREA

FWD

A

FR60 FR61 FR62 FR63

A

Z150

A_SB_530390_6_SBAA_02_00

Figure A-GSBAA - Sheet 02

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0390

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@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

MANDATORY MANDATORY MANDATORY

ATA SYSTEM: 53

TITLE: FUSELAGE - STRUCTURE - INSPECT FOR CROSSBEAM AT

JUNCTION WITH LOWER DECK CARGO DOOR ACTUATOR BEAM AT

FR22/23 AND FR61/FR62

MODIFICATION No.: None

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

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

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

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

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

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

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

AIRBUS prior written consent.

1. PLANNING INFORMATION

**CONF ALL

A. EFFECTIVITY

(1) Models

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 0044-0045 0047 0053 0055 0074-0075 0078-0080 0082-0085 0090

0094-0095 0100-0101 0105 0107 0116-0117 0121 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 0271 0274

0277 0289 0292 0299 0302 0304

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SERVICE BULLETIN

(3) Effectivity by Operator

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

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

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

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

OPERATOR MSN

50W 0003

72U 0079

AFG 0180 0190

BCS 0095 0116 0148 0150 0152 0184 0189 0199 0208 0219 0220 0234

0235 0236 0250 0259 0274 0289

DHL 0084 0085 0141 0149 0249 0265

F2I 0083 0094 0128 0133 0135 0136 0137 0156 0170 0243

FLM 0082 0151 0176 0256

IAW 0239

IRA 0080 0139 0173 0185 0187 0226

IRB 0299 0302

IRM 0055 0090 0160 0175 0204 0244

KZU 0041 0044 0101 0117

MIX 0125 0134 0157 0196 0203 0218

MNB 0019 0047 0123 0212 0277 0292 0304

MSR 0200 0255

NTR 0124 0155 0210 0227 0247 0261

RUN 0075 0105 0107 0121 0147 0154 0183

SOP 0126

TDX 0053 0100 0211 0216 0271

TNO 0045 0074 0078

TSY 0129

(4) Configuration by MSN

MSN CONFIGURATION

0003 0019 0041 0044 0045 0047 0053 0055 0074 0075 0078

0079 0080 0082 0084 0085 0090 0094 0095 0100 0101 0105

0107 0116 0117 0121 0123 0124 0125 0126 0128 0129 0133

0134 0135 0136 0137 0139 0141 0147 0148 0149 0150 0151

0152 0154 0155 0156 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

0271 0274 0289 0299 0302 0304

001

0083 0212 0256 0277 0292 002

(5) Configuration definition

**CONF 001

Config. 001 is valid for all passenger aircraft.

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0390

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SERVICE BULLETIN

**CONF 002

Config. 002 is valid for freighter aircraft.

(6) Material Effectivity

MATERIAL QTY PER A/C SEE NOTES

Standard tool TOOLD01 2

B. CONCURRENT REQUIREMENTS

None

C. REASON

(1) History

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

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

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

in the fastener hole propagating vertically. The design of FWD and AFT cargo door

attachments are similar to the crossbeams at FR22/23 and FR61/FR62 and should be

inspected.

On passenger aircraft, in case of cracks being present in a crossbeam (upper and lower

web), the floor grid cannot withstand ultimate load condition. On freighter aircraft this is

not the case due to different load distribution via the pallets.

(2) Objective/Action

This Service Bulletin details the inspection procedure for aircraft on which the

crossbeams are not previously repaired by the Structure Repair Manual (SRM) or a

Repair Approval Sheet (RAS).

This inspection procedure details :

- High Frequency Eddy Current inspection which will inspect the crossbeams for

cracks at FR22/23 and FR61/62 on passenger aircraft,

- High Frequency Eddy Current and a Ultra Sonic inspection which will inspect the

crossbeam for crack(s) at FR22/23 on freighter aircraft,

- High Frequency Eddy Current inspection which will inspect the crossbeam for

cracks at FR61/62 on freighter aircraft,

before the accumulation of 10000 total aircraft flight cycles.

NOTE: For aircraft on which the crossbeams have been previously repaired by

the Structure Repair Manual (SRM) or a Repair Approval Sheet (RAS)

the operator has to contact AIRBUS before reaching the threshold or the

grace period for further instructions.

In the case no crack(s) are found :

- repeat this inspection at an interval not to exceed 600 Flight Cycles (FC)

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0390

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SERVICE BULLETIN

or

- accomplish the Modification Service Bulletin A300-53-0389 within 600 Flight Cycles

(FC) after the last inspection in accordance with this Inspection Service Bulletin.

. The accomplishment of Modification Service Bulletin No. A300-53-0389 cancels

the requirements of this Inspection Service Bulletin.

In the case crack(s) are found :

- longer than 7.0mm 0.27in.) contact AIRBUS before the next flight and follow their

instructions.

- smaller than or equal to 7.0mm 0.27in.) contact AIRBUS before the next flight and

follow their instructions within :

. 10FC, if crack(s) were detected by Ultra Sonic inspection procedure,

. 50FC, if crack(s) were detected by a High Frequency Eddy Current inspection

procedure.

(3) Advantages

The accomplishment of this Service Bulletin :

- monitors the structure surrounding the rivet heads on crossbeams at FR22/23 and

FR61/62

- can prevent heavy repair.

The accomplishment of Modification Service Bulletin No. A300-53-0389 cancels the

requirements of this Inspection Service Bulletin.

NOTE: This Service Bulletin is mandatory for all passenger aircraft,

recommended for freighter aircraft.

NOTE: If operators have previously accomplished the Modification Service

Bulletin No. A300-53-0389, the accomplishment of this Inspection

Service Bulletin is no longer required.

(4) Operational/Maintenance Consequences

None

D. DESCRIPTION

To accomplish this Service Bulletin it is necessary to :

**CONF 001

Task 530390-832-848-001: Inspection

(1) Special detailed HFEC Inspection for crack(s) at FR22/23 and FR61/62

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0390

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SERVICE BULLETIN

**CONF 002

Task 530390-832-848-001: Inspection

(1) Special detailed HFEC and US inspection for crack(s) at FR22/23 and a special

detailed HFEC inspection for crack(s) at FR61/FR62

**CONF ALL

E. COMPLIANCE

(1) Classification

MANDATORY

(2) Accomplishment Timescale

**CONF 001

COMPLIANCE TIME

(whichever occurs later)

CONDITION ACTION

THRESHOLD GRACE PERIOD

REPETITIVE

INTERVAL NOT

TO EXCEED

If crossbeams

FR22/23 and

FR61/FR62 have

been repaired

previously by SRM

or RAS

Before reaching the

threshold or grace

period contact

Airbus for further

instructions

If crossbeams

FR22/23 and

FR61/FR62 have

not been repaired

previously by SRM

or RAS

Inspect in

accordance with

SUBTASK

530390-832-202-001

(Special detailed

HFEC inspection)

crossbeams for

crack(s) at FR22/23

and FR61/FR62

Before the

accumulation of

10000 total Flight

Cycles (FC)

600FC from

Service Bulletin

issuance

If the crack length is smaller than or

equal to 7.0mm 0.27in.) contact

AIRBUS before the next flight and

follow their instructions within 50FC

Crack(s) found Contact Airbus for Not applicable

further instructions

If a crack length is longer than 7.0mm

0.27in.) contact AIRBUS before the

next flight and follow their instructions

Not applicable

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0390

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SERVICE BULLETIN

Accomplish Service

Modification Bulletin

No. A300-53-0389

Accomplish the Modification Service

Bulletin A300-53-0389 within 600FC

after the last inspection in accordance

with this Inspection Service Bulletin

Not applicable

or

No Crack(s) found

Repeat the

inspection

600FC

Table 1 : Special detailed HFEC inspection for cracks at FR22/23 and FR61/FR62

The accomplishment of Modification Service Bulletin Nos. A300-53-0389 cancels the

requirements of this Inspection Service Bulletin.

Accomplishment of this Service Bulletin is expected to be rendered mandatory for

passenger aircraft by the issue of an Airworthiness Directive (AD) published by the

European Aviation Safety Agency (EASA). It is anticipated that the AD will confirm the

(thresholds and/or intervals and/or date) given above but reference should be made to

the AD for confirmation of the mandated accomplishment timescale.

**CONF 002

COMPLIANCE TIME

(whichever occurs later)

CONDITION ACTION

THRESHOLD GRACE PERIOD

REPETITIVE

INTERVAL NOT

TO EXCEED

If crossbeams

FR22/23 and

FR61/FR62 have

been repaired

previously by SRM

or RAS

Before reaching the

threshold or grace

period contact

Airbus for further

instructions

If crossbeams

FR22/23 and

FR61/FR62 have

not been repaired

previously by SRM

or RAS

Inspect in

accordance with

SUBTASK

530390-832-202-005

(Special detailed

HFEC and US

inspection)

crossbeams for

crack(s) at FR22/23

and (Special

detailed HFEC)

crossbeams for

crack(s) at

FR61/FR62

Before the

accumulation of

10000 total Flight

Cycles (FC)

600FC from

Service Bulletin

issuance

If the crack length is smaller than or

equal to 7.0mm 0.27in.) contact

AIRBUS before the next flight and

follow their instructions within 50FC

Crack(s) found by Not applicable

HFEC inspection

at FR22, FR61 or

FR62

Contact Airbus for

further instructions

If a crack length is longer than 7.0mm

0.27in.) contact AIRBUS before the

next flight and follow their instructions

Not applicable

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SERVICE BULLETIN

If the crack length is smaller than or

equal to 7.0mm 0.27in.) contact

AIRBUS before the next flight and

follow their instructions within 10FC

Crack(s) found by Not applicable

US inspection at

FR23

Contact Airbus for

further instructions

If a crack length is longer than 7.0mm

0.27in.) contact AIRBUS before the

next flight and follow their instructions

Not applicable

Accomplish Service

Modification Bulletin

No. A300-53-0389

Accomplish the Modification Service

Bulletin A300-53-0389 within 600FC

after the last inspection in accordance

with this Inspection Service Bulletin

Not applicable

or

No Crack(s) found

Repeat the

inspection

600FC

Table 1: Special detailed HFEC and US inspection for cracks at FR22/23 and Special detailed HFEC

inspection at FR61/FR62

The accomplishment of Modification Service Bulletin Nos. A300-53-0389 cancels the

requirements of this Inspection Service Bulletin.

The inspection program as stated in this Inspection Service Bulletin (ISB) is mandatory

for the aircraft MSNs 0083, 0212 and 0256 because these aircraft can be used as

passenger aircraft, as per original Airbus design at delivery.

Accomplishment of this Service Bulletin is recommended for freighter aircraft.

**CONF ALL

F. APPROVAL

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

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

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

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

before incorporation of the Service Bulletin.

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

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

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

Bulletins for the converted aircraft.

G. MANPOWER

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

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

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

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

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

included.

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SERVICE BULLETIN

**CONF 001

Task 530390-832-848-001: Inspection

Get Access 4.00

On Aircraft

Special detailed HFEC Inspection for crack(s) at

FR22/23 and FR61/62

0.50

Close-Up 3.00

TOTAL MANHOURS 7.50

ELAPSED TIME (HOURS) 4.00

**CONF 002

Task 530390-832-848-001: Inspection

Get Access 4.00

On Aircraft

Special detailed HFEC and US inspection for crack(s)

at FR22/23 and a special detailed HFEC inspection for

crack(s) at FR61/FR62

0.50

Close-Up 3.00

TOTAL MANHOURS 7.50

ELAPSED TIME (HOURS) 4.00

**CONF ALL

H. WEIGHT AND BALANCE

Not Changed

I. ELECTRICAL LOAD DATA

Not Changed

J. REFERENCES

**CONF 001

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

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

25-55-10 52-30-00 52-33-18

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

Non Destructive Test Manual (NTM) 51-31-05

Service Bulletin (SB) A300-53-0389

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SERVICE BULLETIN

**CONF 002

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

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

25-55-10 52-30-00 52-33-18

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

Non Destructive Test Manual (NTM) 51-21-04 51-31-05

Service Bulletin (SB) A300-53-0389

**CONF ALL

K. PUBLICATION AFFECTED

Not Applicable

L. INTERCHANGEABILITY/MIXABILITY

Not Applicable

M. SPARES

None

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SERVICE BULLETIN

2. MATERIAL INFORMATION

**CONF ALL

A. MATERIAL - PRICE AND AVAILABILITY

(1) Procurement Addresses

None

(2) Price and Availability

None

B. INDUSTRY SUPPORT INFORMATION

None

C. LIST OF COMPONENTS

No Kit

D. LIST OF MATERIALS - OPERATOR SUPPLIED

None

E. PARTS TO BE RE-IDENTIFIED BY OPERATOR

None

F. TOOLING

(1) Tooling - Price and Availability

None

(2) Tools

Standard tool TOOLD01

ITEM TOOL N ̊ TOOL NAME QTY SEE

NOTES

98A52307523000 Support Struts - Fwd And Aft

Cargo Compartment Doors

2 (1)

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

(3) Special Tools

None

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SERVICE BULLETIN

3. ACCOMPLISHMENT INSTRUCTIONS

Task 530390-832-848-001 - Inspection

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

INCLUDED IN THE REFERENCED PROCEDURES

CAUTION: ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP ELECTRICAL

WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY AND

MECHANICALLY SERVICEABLE).

WHEN YOU DO MAINTENANCE WORK, REPAIRS OR MODIFICATIONS,

ALWAYS KEEP ELECTRICAL WIRING, COMPONENTS AND THE WORK AREA

AS CLEAN AS POSSIBLE. TO DO THIS :

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

NECESSARY ON ELECTRICAL WIRING AND COMPONENTS

- REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND

OTHER CONTAMINATION.

THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION

AND DAMAGE TO THE ELECTRICAL WIRING INSTALLATION.

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

Task Associated Data

**CONF 001

Zone

120 130 150

Access

Door 811 812

Manpower

TOTAL MANHOURS 7.50

ELAPSED TIME (HOURS) 4.00

**CONF 002

Zone

120 130 150

Access

Door 811 812

Manpower

TOTAL MANHOURS 7.50

ELAPSED TIME (HOURS) 4.00

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0390

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

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@A300

SERVICE BULLETIN

**CONF ALL

A. GENERAL

**CONF 001

(1) Subtask 530390-910-201-001 - Standard Practices

Work Zones and Access Panels

Zone Access/Work location

130 Access Door 811

Work location from Frame 22, Seat Track 4/5 to Frame 23,

Seat Track 4/5

150 Access Door 812

Work location from Frame 61, Seat Track 4/5 to Frame 62,

Seat Track 4/5

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-41-53, Page Block 001

(a) For the location of access panels (Refer to AMM 06-41-53, Page Block 001).

(2) Subtask 530390-839-201-001 - Documentation

Manpower Resources

Skills NON SPECIFIC

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

Service Bulletin.

**CONF 002

(1) Subtask 530390-910-201-001 - Standard Practices

Work Zones and Access Panels

Zone Access/Work location

130 Access Door 811

Work location from Frame 22, Seat Track 4/5 to Frame 23,

Seat Track 4/5

150 Access Door 812

Work location from Frame 61, Seat Track 4/5 to Frame 62,

Seat Track 4/5

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-41-53, Page Block 001

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0390

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

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SERVICE BULLETIN

(a) For the location of access panels (Refer to AMM 06-41-53, Page Block 001).

(2) Subtask 530390-839-201-001 - Documentation

Manpower Resources

Skills NON SPECIFIC

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

Service Bulletin.

**CONF ALL

B. PREPARATION

**CONF 001

(1) Subtask 530390-941-201-001 - Job Set-up

Work Zones and Access Panels

Zone Access/Work location

130 Access Door 811

Work location from Frame 22, Seat Track 4/5 to Frame 23,

Seat Track 4/5

150 Access Door 812

Work location from Frame 61, Seat Track 4/5 to Frame 62,

Seat Track 4/5

Manpower Resources

Skills NON SPECIFIC

Material necessary to do the job

Standard tool TOOLD01

ITEM TOOL N ̊ TOOL NAME QTY SEE

NOTES

98A52307523000 Support Struts - FWD and

AFT Cargo Compartment

Doors

2 (1)

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

References

Aircraft Maintenance Manual (AMM) 24-00-00, Page Block 301

24-41-00, Page Block 301

25-51-00, Page Block 401

25-51-11, Page Block 401

25-55-10, Page Block 201

52-30-00, Page Block 301

52-33-18, Page Block 401

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

Block 301).

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0390

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

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SERVICE BULLETIN

(b) Put access platform(s) in position

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

301).

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

301).

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

301).

(f) Secure the FWD and AFT cargo-compartment doors with :

98A52307523000 Support Struts -

FWD and AFT

Cargo

Compartment Doors

2

or with the door actuator safety lock(s).

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

(g) Remove the FWD cargo-compartment ceiling panel 132BT (Refer to AMM

25-51-11, Page Block 401).

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

(i) Remove the AFT cargo-compartment ceiling panels 152FT and 152GT (Refer to

AMM 25-55-10, Page Block 201).

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

(2) Subtask 530390-865-201-001 - C/B Opening

Work Zones and Access Panels

Zone Access/Work location

120

Manpower Resources

Skills ELECTRICAL

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

PANEL DESIGNATION FIN LOCATION SEE

NOTES

128VU HYDRAULIC/ACCU PRESS

CTL AND CARGO PUMP

7GX 803/C11

101VU ELEC HYD PUMP 23GX ALT2

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

location given in the table.

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0390

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

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@A300

SERVICE BULLETIN

**CONF 002

(1) Subtask 530390-941-201-001 - Job Set-up

Work Zones and Access Panels

Zone Access/Work location

130 Access Door 811

Work location from Frame 22, Seat Track 4/5 to Frame 23,

Seat Track 4/5

150 Access Door 812

Work location from Frame 61, Seat Track 4/5 to Frame 62,

Seat Track 4/5

Manpower Resources

Skills NON SPECIFIC

Material necessary to do the job

Standard tool TOOLD01

ITEM TOOL N ̊ TOOL NAME QTY SEE

NOTES

98A52307523000 Support Struts - FWD and

AFT Cargo Compartment

Doors

2 (1)

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

References

Aircraft Maintenance Manual (AMM) 24-00-00, Page Block 301

24-41-00, Page Block 301

25-51-00, Page Block 401

25-51-11, Page Block 401

25-55-10, Page Block 201

52-30-00, Page Block 301

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.: A300-53-0390

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

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(f) Secure the FWD and AFT cargo-compartment doors with :

98A52307523000 Support Struts -

FWD and AFT

Cargo

Compartment Doors

2

or with the door actuator safety lock(s).

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

(g) Remove the FWD cargo-compartment ceiling panel 132BT (Refer to AMM

25-51-11, Page Block 401).

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

(i) Remove the AFT cargo-compartment ceiling panels 152FT and 152GT (Refer to

AMM 25-55-10, Page Block 201).

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

(2) Subtask 530390-865-201-001 - C/B Opening

Work Zones and Access Panels

Zone Access/Work location

120

Manpower Resources

Skills ELECTRICAL

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

PANEL DESIGNATION FIN LOCATION SEE

NOTES

128VU HYDRAULIC/ACCU PRESS

CTL AND CARGO PUMP

7GX 803/C11

101VU ELEC HYD PUMP 23GX ALT2

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

location given in the table.

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0390

REVISION No.: 00 - Jan 15/10 Page: 18

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SERVICE BULLETIN

**CONF ALL

C. PROCEDURE

**CONF 001

(1) Subtask 530390-832-202-001 - Special detailed HFEC Inspection for crack(s) at

FR22/23 and FR61/62

Work Zones and Access Panels

Zone Access/Work location

120 Access Door 811

Work location from Frame 22, Seat Track 4/5 to Frame 23,

Seat Track 4/5

150 Access Door 812

Work location from Frame 61, Seat Track 4/5 to Frame 62,

Seat Track 4/5

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills NON DESTRUCTIVE

TESTING

References

Non Destructive Test Manual (NTM) 51-31-05 Part 1

Service Bulletin (SB) A300-53-0389

Fig. A-GBAAA

HFEC Inspection for Cracks between

FR22/23

Sheet 01

Sheet 02

Fig. A-GFAAA

Flow-Chart : HFEC Inspection for Cracks

between FR22/23 and FR61/62

Sheet 01

Fig. A-GBFAA

HFEC Inspection for Cracks between

FR61/62

Sheet 01

Sheet 02

(a) Check if the crossbeams between :

- FR22 and FR23 and

- FR61 and FR62

have been previously repaired by SRM or RAS.

1 In the case the crossbeams are previously repaired by SRM or RAS contact

AIRBUS and follow their instructions.

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0390

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2 In the case the crossbeams are not previously repaired by SRM or RAS :

a Perform the special detailed HFEC Inspection for crack(s) in the area

around the rivet heads at FR22 and FR23.

Refer to NTM 51-31-05 Part 1

Refer to Fig. A-GBAAA Sheet 02, Details B and C

Refer to Fig. A-GFAAA Sheet 01

b Perform the special detailed HFEC Inspection for crack(s) in the areas

around the rivet heads at FR61 and FR62.

Refer to NTM 51-31-05 Part 1

Refer to Fig. A-GBFAA Sheet 02, Details B and C

Refer to Fig. A-GFAAA Sheet 01

c In the case no crack(s) is/are found :

<1> Repeat the inspection at interval not to exceed 600FC

or

<2> Accomplish Service Bulletin No. A300-53-0389 within 600FC after

the last inspection in accordance with this Inspection Service

Bulletin.

No further action is required in accordance with this Service Bulletin.

d In the case crack(s) is/are found :

<1> In the case the crack(s) is/are longer than 7.0mm (0.27in.) :

<a> Contact AIRBUS before the next flight and follow their

instructions.

<b> No further action is required in accordance with this Service

Bulletin.

<2> In the case the crack(s) is/are crack(s) smaller than or equal to

7.0mm (0.27in.) :

<a> Contact AIRBUS before the next flight and follow their

instructions within the next 50FC.

<b> No further action is required in accordance with this Service

Bulletin.

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0390

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

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SERVICE BULLETIN

**CONF 002

(1) Subtask 530390-832-202-005 - Special detailed HFEC and US inspection for

crack(s) at FR22/23 and a special detailed HFEC inspection for crack(s) at

FR61/FR62

Work Zones and Access Panels

Zone Access/Work location

120 Access Door 811

Work location from Frame 22, Seat Track 4/5 to Frame 23,

Seat Track 4/5

150 Access Door 812

Work location from Frame 61, Seat Track 4/5 to Frame 62,

Seat Track 4/5

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills NON DESTRUCTIVE

TESTING

References

Non Destructive Test Manual (NTM) 51-21-04 Part 1

51-31-05 Part 1

Service Bulletin (SB) A300-53-0389

Fig. A-GBCAA

HFEC Inspection for cracks between

FR22/23

Sheet 01

Sheet 02

Fig. A-GBDAA

US Inspection for Cracks between

FR22/23

Sheet 01

Sheet 02

Fig. A-GBFAA

HFEC Inspection for Cracks between

FR61/62

Sheet 01

Sheet 02

Fig. A-GFBAA

Flow-Chart : HFEC and US Inspection

for cracks between FR22/23 and HFEC

Inspection for cracks at FR61/62

Sheet 01

Sheet 02

(a) Check if the crossbeams between :

- FR22 and FR23 and

- FR61 and FR62

have been previously repaired by SRM or RAS.

1 In the case the crossbeams are previously repaired by SRM or RAS contact

AIRBUS and follow their instructions.

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0390

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

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2 In the case the crossbeams are not previously repaired by SRM or RAS :

a Perform a special detailed HFEC Inspection for crack(s) in the area

around the rivet heads at FR22.

Refer to NTM 51-31-05 Part 1

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

Refer to Fig. A-GBFAA Sheet 01

Refer to Fig. A-GFBAA Sheet 01

b Perform a special detailed Ultra Sonic Inspection for crack(s) in the area

around the rivet heads at FR23.

Refer to NTM 51-21-04 Part 1

Refer to Fig. A-GBDAA Sheet 02, Detail B

Refer to Fig. A-GFBAA

c Perform a special detailed HFEC Inspection for crack(s) in the areas

around the rivet heads at FR61 and FR62.

Refer to NTM 51-31-05 Part 1

Refer to Fig. A-GBFAA Sheet 02, Details B and C

Refer to Fig. A-GFBAA Sheet 02

d In the case no crack(s) is/are found :

<1> Repeat the inspection at interval not to exceed 600FC

or

<2> Accomplish Service Bulletin No. A300-53-0389 within 600FC after

the last inspection in accordance with this Inspection Service

Bulletin.

No further action is required in accordance with this Service Bulletin.

e In the case crack(s) is/are found :

<1> In the case the crack(s) is/are longer than 7.0mm (0.27in.) :

<a> Contact AIRBUS before the next flight and follow their

instructions.

<b> No further action is required in accordance with this Service

Bulletin.

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0390

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

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<2> In the case the crack(s) is/are crack(s) smaller than or equal to

7.0mm (0.27in.) :

<a> Contact AIRBUS before the next flight and follow their

instructions within the next :

50FC, if crack(s) were detected by HF-Eddy Current inspection

procedure, or

10FC, if crack(s) were detected by Ultra Sonic inspection

procedure.

<b> No further action is required in accordance with this Service

Bulletin.

**CONF ALL

D. TEST

**CONF 001

(1) Subtask 530390-700-201-001 - Testing

Manpower Resources

Skills NON SPECIFIC

None

**CONF 002

(1) Subtask 530390-700-201-001 - Testing

Manpower Resources

Skills NON SPECIFIC

None

**CONF ALL

E. CLOSE-UP

**CONF 001

(1) Subtask 530390-865-202-001 - C/B Closing

Work Zones and Access Panels

Zone Access/Work location

120

Manpower Resources

Skills ELECTRICAL

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0390

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

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

PANEL DESIGNATION FIN LOCATION SEE

NOTES

128VU HYDRAULIC/ACCU PRESS

CTL AND CARGO 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.

(2) Subtask 530390-942-201-001 - Close-up

Manpower Resources

Skills AIRFRAME

References

Aircraft Maintenance Manual (AMM) 25-51-11, Page Block 401

25-52-11, Page Block 401

52-30-00, Page Block 301

(a) Install the FWD cargo-compartment ceiling panel 132BT (Refer to AMM 25-51-11,

Page Block 401).

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

(c) Install the AFT cargo-compartment ceiling panel 152FT and 152GT (Refer to AMM

25-52-11, Page Block 401).

(d) Install the door actuator lining between FR61 and FR62.

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

equipment.

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

FWD and AFT cargo-compartment door.

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

301).

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

301).

(i) Remove the access platform(s).

**CONF 002

(1) Subtask 530390-865-202-001 - C/B Closing

Work Zones and Access Panels

Zone Access/Work location

120

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0390

REVISION No.: 00 - Jan 15/10 Page: 24

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@A300

SERVICE BULLETIN

Manpower Resources

Skills ELECTRICAL

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

PANEL DESIGNATION FIN LOCATION SEE

NOTES

128VU HYDRAULIC/ACCU PRESS

CTL AND CARGO 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.

(2) Subtask 530390-942-201-001 - Close-up

Manpower Resources

Skills AIRFRAME

References

Aircraft Maintenance Manual (AMM) 25-51-11, Page Block 401

25-52-11, Page Block 401

52-30-00, Page Block 301

(a) Install the FWD cargo-compartment ceiling panel 132BT (Refer to AMM 25-51-11,

Page Block 401).

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

(c) Install the AFT cargo-compartment ceiling panel 152FT and 152GT (Refer to AMM

25-52-11, Page Block 401).

(d) Install the door actuator lining between FR61 and FR62.

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

equipment.

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

FWD and AFT cargo-compartment door.

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

301).

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

301).

(i) Remove the access platform(s).

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0390

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

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@A300

SERVICE BULLETIN

**CONF 001

SEAT TRACK 5

SEAT TRACK 3

SEAT TRACK 2

SEAT TRACK 4

FR21 FR22 FR23 FR24

SEAT TRACK 6

A_SB_530390_6_BAAA_01_00

Z130

A

B C

FWD

A

Figure A-GBAAA - Sheet 01

HFEC Inspection for Cracks between FR22/23

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0390

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

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@A300

SERVICE BULLETIN

**CONF 001

A_SB_530390_6_BAAA_02_01

NOTE:

01

VIEW LOOKING AFT

VIEW LOOKING FWD

FR22

FR23

(AROUND RIVET HEADS), REFER TO NTM 51−31−05 PART1

D

01

01

01

01

D

B

C

INSPECTION AREA FOR THE HFEC INSPECTION

D

TYPICAL

02

02 POSSIBLE CRACK IN CROSSBEAM STRUCTURE 

BENEATH INSPECTION AREA

Figure A-GBAAA - Sheet 02

HFEC Inspection for Cracks between FR22/23

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0390

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

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SERVICE BULLETIN

**CONF 002

SEAT TRACK 5

SEAT TRACK 3

SEAT TRACK 2

SEAT TRACK 4

FR21 FR22 FR23 FR24

SEAT TRACK 6

Z130

A

B

FWD

A

A_SB_530390_6_BCAA_01_00

Figure A-GBCAA - Sheet 01

HFEC Inspection for cracks between FR22/23

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0390

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

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@A300

SERVICE BULLETIN

**CONF 002

NOTE:

POSSIBLE CRACK IN CROSSBEAM STRUCTURE

01

VIEW LOOKING AFT

FR22

(AROUND RIVET HEADS), REFER TO NTM 51−31−05 PART1

01

01

02

TYPICAL

02

01

01

B

C

C

INSPECTION AREA FOR THE HFEC INSPECTION

AREA 1

BENEATH INSPECTION AREA A_SB_530390_6_BCAA_02_01

Figure A-GBCAA - Sheet 02

HFEC Inspection for cracks between FR22/23

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0390

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

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@A300

SERVICE BULLETIN

**CONF 002

SEAT TRACK 5

SEAT TRACK 3

SEAT TRACK 2

SEAT TRACK 4

FR21 FR22 FR23 FR24

SEAT TRACK 6

Z130

A

B

FWD

A

A_SB_530390_6_BDAA_01_00

Figure A-GBDAA - Sheet 01

US Inspection for Cracks between FR22/23

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0390

REVISION No.: 00 - Jan 15/10 Page: 30

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@A300

SERVICE BULLETIN

**CONF 002

NOTE:

POSSIBLE CRACK IN CROSSBEAM STRUCTURE

01

(AROUND RIVET HEADS), FOR INSPECTION REFER TO NTM 51−21−04 PART1

02

US INSPECTION AREA

01

01

VIEW LOOKING AFT

C

02

B

03

03 SEARCH UNIT SCAN MOVEMENT LINE

C

AREA 2

A_SB_530390_6_BDAA_02_02

FR23

Figure A-GBDAA - Sheet 02

US Inspection for Cracks between FR22/23

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0390

REVISION No.: 00 - Jan 15/10 Page: 31

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SERVICE BULLETIN

**CONF ALL

A_SB_530390_6_BFAA_01_00

SEAT TRACK 5

SEAT TRACK 3

SEAT TRACK 2

SEAT TRACK 4

A

SEAT TRACK 6

FR60 FR61 FR62 FR63

Z150

FWD

A

B C

Figure A-GBFAA - Sheet 01

HFEC Inspection for Cracks between FR61/62

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0390

REVISION No.: 00 - Jan 15/10 Page: 32

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@A300

SERVICE BULLETIN

**CONF ALL

NOTE:

POSSIBLE CRACK IN CROSSBEAM STRUCTURE 

01

VIEW LOOKING AFT

VIEW LOOKING FWD

FR61

FR62

(AROUND RIVET HEADS), REFER TO NTM 51−31−05 PART1

01

01

01

01

B

C

02

D

TYPICAL

02

INSPECTION AREA FOR THE HFEC INSPECTION

D

D

BENEATH INSPECTION AREA A_SB_530390_6_BFAA_02_01

Figure A-GBFAA - Sheet 02

HFEC Inspection for Cracks between FR61/62

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0390

REVISION No.: 00 - Jan 15/10 Page: 33

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SERVICE BULLETIN

**CONF 001

YES

NO

BEFORE REACHING

THE THRESHOLD OR

GRACE PERIOD

CRACK FINDINGS

YES

CRACK LENGTH

MORE THAN

7.0mm (0.28 in.)

NO

OR

REPEAT THE 

INSPECTION

AT INTERVAL

NO YES

NO FURTHER ACTION IS 

REQUIRED IN ACCORDANCE

WITH THIS INSPECTION

SERVICE BULLETIN

FR22/23 AND FR61/62,

REPAIRED BY SRM OR RAS

PREVIOUSLY

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

 HFEC INSPECTION OF THE CROSSBEAMS,

REFER TO NTM 51−10−08, PB 601

CROSSBEAMS,

AT THE THRESHOLD DETAILED IN 

NOT TO

EXCEED 600FC

CONTACT AIRBUS

BEFORE THE NEXT

FLIGHT AND FOLLOW

THEIR INSTRUCTIONS

WITHIN 50FC

CONTACT AIRBUS

BEFORE THE NEXT

FLIGHT AND FOLLOW

THEIR INSTRUCTIONS

ACCOMPLISH SERVICE BULLETIN

NO. A300−53−0389

WITHIN 600FC AFTER THE LAST

INSPECTION IN ACC. WITH THIS

INSPECTION SERVICE BULLETIN

A_SB_530390_6_FAAA_01_04

CONTACT AIRBUS

AND FOLLOW THEIR

INSTRUCTIONS

Figure A-GFAAA - Sheet 01

Flow-Chart : HFEC Inspection for Cracks between FR22/23 and FR61/62

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0390

REVISION No.: 00 - Jan 15/10 Page: 34

6

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

SERVICE BULLETIN

**CONF 002

NO YES

CROSSBEAMS,

FR22/23,

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

INSPECTION OF THE 

REFER TO NTM 51−21−04 PART1

IN AREA 1 OR

AND 2

AT INTERVAL

REFER TO FIGURE A−GBCAA

DO A SPECIAL DETAILED US 

DETAILED HFEC INSPECTION OF 

REFER TO NTM 51−31−05 PART1

REFER TO FIGURE A−GBDAA

CRACK FINDINGS IN

AREA 1 AND/OR AREA 2

YES

CRACK LENGTH

MORE THAN

7.0mm (0.28 in.)

YES

NO FURTHER ACTION IS 

REQUIRED IN ACCORDANCE

WITH THIS INSPECTION

SERVICE BULLETIN

NO

REPEAT THE 

INSPECTION

REPAIRED BY SRM OR RAS

PREVIOUSLY

THE CROSSBEAMS (AREA 1) AT FR22

CROSSBEAMS (AREA 2) AT FR23

AT THE THRESHOLD DETAILED IN 

NOT TO EXCEED

600FC

AREA 1

AT FR22

AREA 2

AT FR23

NO

ACCOMPLISH SERVICE BULLETIN

NO. A300−53−0389

WITHIN 600FC AFTER THE LAST

INSPECTION IN ACC. WITH THIS

 INSPECTION SERVICE BULLETIN

A_SB_530390_6_FBAA_01_05

BEFORE REACHING

THE THRESHOLD OR

GRACE PERIOD

CONTACT AIRBUS

BEFORE THE NEXT

FLIGHT AND FOLLOW

THEIR INSTRUCTIONS

WITHIN 50FC

CONTACT AIRBUS

BEFORE THE NEXT

FLIGHT AND FOLLOW

THEIR INSTRUCTIONS

CONTACT AIRBUS

AND FOLLOW THEIR

INSTRUCTIONS

CONTACT AIRBUS

BEFORE THE NEXT

FLIGHT AND FOLLOW

THEIR INSTRUCTIONS

WITHIN 10FC

Figure A-GFBAA - Sheet 01

Flow-Chart : HFEC and US Inspection for cracks between FR22/23 and HFEC Inspection for cracks at

FR61/62

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0390

REVISION No.: 00 - Jan 15/10 Page: 35

6

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

SERVICE BULLETIN

**CONF 002

YES

NO

FR61/62,

REPAIRED BY SRM OR RAS

PREVIOUSLY

CRACK FINDINGS

YES

CRACK LENGTH

MORE THAN

7.0mm (0.28 in.)

NO

OR

NO YES

NO FURTHER ACTION IS 

REQUIRED IN ACCORDANCE

WITH THIS INSPECTION

SERVICE BULLETIN

CROSSBEAMS,

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

 HFEC INSPECTION OF THE CROSSBEAMS,

REFER TO NTM 51−10−08, PB 601

AT THE THRESHOLD DETAILED IN 

REPEAT THE 

INSPECTION

AT INTERVAL

NOT TO

EXCEED 600FC

ACCOMPLISH SERVICE BULLETIN

NO. A300−53−0389

WITHIN 600FC AFTER THE LAST

INSPECTION IN ACC. WITH THIS

INSPECTION SERVICE BULLETIN

A_SB_530390_6_FBAA_02_04

BEFORE REACHING

THE THRESHOLD OR

GRACE PERIOD

CONTACT AIRBUS

BEFORE THE NEXT

FLIGHT AND FOLLOW

THEIR INSTRUCTIONS

WITHIN 50FC

CONTACT AIRBUS

BEFORE THE NEXT

FLIGHT AND FOLLOW

THEIR INSTRUCTIONS

CONTACT AIRBUS

AND FOLLOW THEIR

INSTRUCTIONS

Figure A-GFBAA - Sheet 02

Flow-Chart : HFEC and US Inspection for cracks between FR22/23 and HFEC Inspection for cracks at

FR61/62

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0390

REVISION No.: 00 - Jan 15/10 Page: 36

6

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

SERVICE BULLETIN

REPORTING SHEET

TITLE: FUSELAGE - STRUCTURE - INSPECT FOR CROSSBEAM AT

JUNCTION WITH LOWER DECK CARGO DOOR ACTUATOR BEAM AT

FR22/23 AND FR61/FR62

MODIFICATION No.: None

Please complete the appropriate item (A or B):

A - SB WILL BE embodied YES/NO (if NO please comment)

If YES, aircraft concerned (as per SB effectivity by default) and planned dates (month/year) of

embodiment:

B - SB HAS BEEN embodied on aircraft:

Operator comments:

From Airline:

Name/Title:

Signature: Date:

If operational documentation is affected (see Paragraph 1.K of this SB): If information is needed prior to

next normal revision or prior to SB embodiment, please indicate required service(s):

Either: Modification Operational Impact (MOI), if available YES/NO

Or : Intermediate revision YES/NO

Important Information: This SB will only be incorporated in your maintenance and operational

documentation if this sheet is returned to Airbus and signed by a duly authorised representative. With

the next feasible revision, this will result in

- Updating of maintenance documentation to show pre and post SB data.

- Updating of maintenance and operational documentation to show post SB data after embodiment.

If this SB requires previous or simultaneous accomplishment of other SBs, Airbus shall automatically

include them in the manual revisions. Refer to SIL 00-037 for detailed information.

Please return this completed sheet to:

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX FRANCE

Attn: SDC32 Technical Data and Documentation Services

FAX: (+33) 5 61 93 28 06

e-mail: sb.reporting@airbus.com

or via your Resident Customer Support Office.

Alternatively, SB lists via letters or fax are also accepted.

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0390

REVISION No.: 00 - Jan 15/10 Page: 1

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@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.: A300-53-0390

REVISION No.: 00 - Jan 15/10 Page: 1

6

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