# @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. 

# MANDATORYMANDATORYMANDATORY 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 6

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# @A300 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

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0390 REVISION No.: 00 - Jan 15/10 Page: 2 6

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# @A300 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

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0390 REVISION No.: 00 - Jan 15/10 Page: 3 6

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# @A300 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 REVISION No.: 00 - Jan 15/10 Page: 4 6

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# @A300 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

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0390 REVISION No.: 00 - Jan 15/10 Page: 5 6

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# @A300 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 REVISION No.: 00 - Jan 15/10 Page: 6 6

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# @A300 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 REVISION No.: 00 - Jan 15/10 Page: 7 6

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# @A300 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 REVISION No.: 00 - Jan 15/10 Page: 8 6

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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



# MANDATORYMANDATORYMANDATORY 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

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0390 REVISION No.: 00 - Jan 15/10 Page: 1 6

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# @A300 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 REVISION No.: 00 - Jan 15/10 Page: 2 6

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# @A300 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 REVISION No.: 00 - Jan 15/10 Page: 3 6

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# @A300 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 REVISION No.: 00 - Jan 15/10 Page: 4 6

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# @A300 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 Not applicable Crack(s) found 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

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0390 REVISION No.: 00 - Jan 15/10 Page: 5 6

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# @A300 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 Not applicable Crack(s) found by 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

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0390 REVISION No.: 00 - Jan 15/10 Page: 6 6

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# @A300 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 Not applicable Crack(s) found by 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. EASA21J.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.
DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0390 REVISION No.: 00 - Jan 15/10 Page: 7 6

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# @A300 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

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0390 REVISION No.: 00 - Jan 15/10 Page: 8 6

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# @A300 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

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0390 REVISION No.: 00 - Jan 15/10 Page: 9 6

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# @A300 SERVICE BULLETIN

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# @A300 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

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0390 REVISION No.: 00 - Jan 15/10 Page: 11 6

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# @A300 SERVICE BULLETIN

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# @A300 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 6

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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 6

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# @A300 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 6

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# @A300 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 6

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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 6

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# @A300 SERVICE BULLETIN (f) Secure the FWD and AFT cargo-compartment doors with : 98A52307523000 Support Struts - FWD and AFT Cargo Compartment Doors 2

or with the door actuator safety lock(s). Refer to AMM 52-30-00, Page Block 301 (g) Remove 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 6

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# @A300 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 REVISION No.: 00 - Jan 15/10 Page: 19 6

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# @A300 SERVICE BULLETIN
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 6

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# @A300 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 6

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# @A300 SERVICE BULLETIN
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 6

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# @A300 SERVICE BULLETIN <2> In the case the crack(s) is/are crack(s) smaller than or equal to 7.0mm (0.27in.) : <a> Contact AIRBUS before the next flight and follow their instructions within the next : 50FC, if crack(s) were detected by HF-Eddy Current inspection procedure, or 10FC, if crack(s) were detected by Ultra Sonic inspection procedure. <b> No further action is required in accordance with this Service Bulletin. **CONF 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 6

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# @A300 SERVICE BULLETIN (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 6

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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 6

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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 6

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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

POSSIBLE CRACK IN CROSSBEAM STRUCTURE 02 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 6

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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_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 6

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

# @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

A_SB_530390_6_BCAA_02_01 BENEATH INSPECTION AREA 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 6

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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 6

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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

SEARCH UNIT SCAN MOVEMENT LINE 03 

## 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 6

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# @A300 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 6

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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**

A_SB_530390_6_BFAA_02_01 BENEATH INSPECTION AREA 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 6

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# @A300 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

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# @A300 SERVICE BULLETIN

**CONF 002

YES NO CROSSBEAMS, FR22/23,

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

INSPECTION OF THE REFER TO NTM 51−21−04 PART1

OR IN AREA 1

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

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# @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

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# @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.