# @A340-500/600 SERVICE BULLETIN REVISION TRANSMITTAL SHEET AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE Tel : (33) 5 61 93 33 33 Telex : AIRBU 530526F Fax : (33) 5 61 93 42 51



# MANDATORY MANDATORY MANDATORY ATA SYSTEM: 55 

### TITLE: STABILIZERS - RUDDER SIDE SHELL SANDWICH REPAIR INSPECTION MODIFICATION No.: None This page transmits Revision No.01 of Service Bulletin No.A340-55-5007 ADDITIONAL WORK **CONF ALL No additional work is required by this revision for aircraft modified by any previous issue. REASON Revision No. 01 issued to embody the local sanding procedure. CHANGES SUMMARY EFFECTIVITY OPERATOR LIST UPDATED R REFERENCES / REPERCUSSIONS REFERENCES/REPERCUSSIONS TABLE UPDATED R PLANNING INFORMATION EFFECTIVITY EFFECTIVITY RELATED INFORMATION UPDATED R COMPLIANCE Accomplishment Timescale ACCOMPLISHMENT TIMESCALE UPDATED R MANPOWER MANPOWER UPDATED R REFERENCES REFERENCED DOCUMENTATION UPDATED R MATERIAL INFORMATION LIST OF MATERIALS - OPERATOR SUPPLIED Consumable Materials Consumable CMLD01 CONSUMABLE MATERIAL SET UPDATED CONSUMABLE UPDATED R TOOLING Tools TOOLS UPDATED R DATE: Feb 07/13 SERVICE BULLETIN No.: A340-55-5007 REVISION No.: 01 - Aug 20/14 Page: 1 6

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# @A340-500/600 SERVICE BULLETIN REVISION TRANSMITTAL SHEET ACCOMPLISHMENT INSTRUCTIONS TASK 555007- 832-848-001-Inspection TASK SOLUTION UPDATED NOTE UPDATED R Subtask 555007-910-201-001 SUBTASK SOLUTION UPDATED QUANTITY UPDATED CONSUMABLE UPDATED MATERIAL LIST UPDATED R
Subtask 555007-941-201-001 SUBTASK SOLUTION UPDATED NOTE UPDATED R Subtask 555007-832-201-001 SUBTASK SOLUTION UPDATED FIGURE REFERENCE UPDATED R Subtask 555007-832-202-001 SUBTASK SOLUTION UPDATED QUANTITY UPDATED CONSUMABLE UPDATED MATERIAL LIST UPDATED FIGURE REFERENCE UPDATED NOTE UPDATED R

Subtask 555007-832-203-001 SUBTASK SOLUTION UPDATED QUANTITY UPDATED CONSUMABLE UPDATED MATERIAL LIST UPDATED FIGURE REFERENCE UPDATED NOTE UPDATED R

Subtask 555007-832-204-001 SUBTASK SOLUTION UPDATED CONSUMABLE UPDATED FIGURE REFERENCE UPDATED NOTE UPDATED CONFIGURATION UPDATED MATERIAL LIST UPDATED R

Subtask 555007-832-205-001 SUBTASK SOLUTION UPDATED QUANTITY UPDATED CONSUMABLE UPDATED MATERIAL LIST UPDATED REFERENCED DOCUMENTATION UPDATED FIGURE REFERENCE UPDATED REFERENCES UPDATED R

Subtask 555007-832-206-001 SUBTASK SOLUTION UPDATED CONSUMABLE UPDATED FIGURE REFERENCE UPDATED NOTE UPDATED MATERIAL LIST UPDATED R

Subtask 555007-832-207-001 SUBTASK SOLUTION UPDATED QUANTITY UPDATED CONSUMABLE UPDATED MATERIAL LIST UPDATED NOTE UPDATED R

DATE: Feb 07/13 SERVICE BULLETIN No.: A340-55-5007 REVISION No.: 01 - Aug 20/14 Page: 2 6

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# @A340-500/600 SERVICE BULLETIN REVISION TRANSMITTAL SHEET Subtask 555007-833-201-001 SUBTASK SOLUTION UPDATED QUANTITY UPDATED CONSUMABLE UPDATED REFERENCED DOCUMENTATION UPDATED MATERIAL LIST UPDATED R

Subtask 555007-832-208-001 SUBTASK SOLUTION ADDED N Subtask 555007-942-201-001 SUBTASK SOLUTION UPDATED R Fig. A-GBFAA Fig. A-GBFAA Sheet 02 SHEET UPDATED R Fig. A-GBHAA FIGURE SOLUTION UPDATED R Fig. A-GBHAA Sheet 01 SHEET UPDATED R Fig. A-GBHAA Sheet 02 SHEET UPDATED R Fig. A-GBHAA Sheet 03 SHEET UPDATED R Fig. A-GBHAA Sheet 04 SHEET ADDED N Fig. A-GFAAA FIGURE SOLUTION UPDATED R Fig. A-GFAAA Sheet 01 SHEET UPDATED R Fig. A-GFAAA Sheet 02 SHEET UPDATED R Fig. A-GFAAA Sheet 03 SHEET UPDATED R Fig. A-GFAAA Sheet 04 SHEET UPDATED R Fig. A-GFAAA Sheet 05 SHEET UPDATED R Fig. A-GFAAA Sheet 06 SHEET ADDED N Fig. A-GAAAA Fig. A-GAAAA Sheet 01 SHEET UPDATED R Fig. A-GABAA Fig. A-GABAA Sheet 04 SHEET UPDATED R Fig. A-GABAA Sheet 08 SHEET UPDATED R FILLING INSTRUCTIONS This Service Bulletin has been generated electronically and is reissued as a complete document. Replace the complete document. Put this Revision Transmittal Sheet in front of the Service Bulletin. HISTORY OF PREVIOUS REVISIONS No previous revision REVISION SEQUENCE ORIGINAL: Feb 07/13 REVISION No. : 01 - Aug 20/14

DATE: Feb 07/13 SERVICE BULLETIN No.: A340-55-5007 REVISION No.: 01 - Aug 20/14 Page: 3 6

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# @A340-500/600 SERVICE BULLETIN REVISION TRANSMITTAL SHEET

This Page Intentionally Left Blank

DATE: Feb 07/13 SERVICE BULLETIN No.: A340-55-5007 REVISION No.: 01 - Aug 20/14 Page: 4 6

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# @A340-500/600 SERVICE BULLETIN SUMMARY AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE Tel : (33) 5 61 93 33 33 Telex : AIRBU 530526F Fax : (33) 5 61 93 42 51 This summary is for information only and is not approved for modification of the aircraft. 

# MANDATORY MANDATORY MANDATORY ATA SYSTEM: 55 

### TITLE: STABILIZERS - RUDDER SIDE SHELL SANDWICH REPAIR INSPECTION **CONF ALL MODIFICATIONS None REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES On AIRBUS Single Aisle, Long Range and Wide Body family aircraft, the rudder side shell is a sandwich structure made of Carbon Fiber Reinforced Plastic (CFRP) and Glass Fiber Reinforced Plastic (GFRP) with a honeycomb core. A case of skin damage was reported on a composite side panel of a rudder installed on an A310 aircraft. Investigations have shown that the damage started from a skin panel area previously repaired in-service. This repair was performed as per A310 SRM 55-41-12 Fig. 204 procedure. The new damage has been identified as a damage between the core and the skin in the repaired area. This new damage has developed during normal operations due to the variation of pressure during ground-air-ground cycles. Following the above mentioned damage scenario, it has been identified that SRM procedures need to be improved to ensure an adequate repair quality. An improper bonding between skin and core during a repair may lead to a damage initiation and propagation, which may not be detectable visually. A large rudder damage, resulting from an undetected damage growth, could affect the handling quality of the aircraft. This Service Bulletin details the inspection procedure to inspect affected rudders fitted on A340 aircraft for potential damage. Different inspection procedures are necessary: - Pulse thermography inspection - Elasticity Laminate Checker (ELCH) inspection - Ultrasonic Testing (UT) inspection. - Tap test inspection. DATE: Feb 07/13 SERVICE BULLETIN No.: A340-55-5007 REVISION No.: 01 - Aug 20/14 Page: 1 6

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# @A340-500/600 SERVICE BULLETIN SUMMARY The accomplishment of this Service Bulletin will contribute to detect potential damage around in-service repairs accomplished on rudders made of Carbon Fiber Reinforced Plastic (CFRP) and Glass Fiber Reinforced Plastic (GFRP) with a honeycomb core. GENERAL EVALUATION EVALUATION TABLE COMPLIANCE MANDATORY (1) CANCELS INSPECTION SB NO POTENTIAL AD YES A/C OPERATION AFFECTED NO RELIABILITY AFFECTED NO PAX COMFORT AFFECTED NO COST SAVING NO LROPS AFFECTED NO STRUCTURAL LIFE EXTN NO VENDOR SB INVOLVED NO NOTE (1) : Service Bulletin must be accomplished. MATERIAL PRICE INFORMATION No Material EFFECTIVITY This Service Bulletin is applicable to this (these) operator(s) :

06U 25R 36V 70U 72W AHY AIB CES CHH DLH ETD HFM HFY IBE QAF QTR SAA SIA TAM THA UAE VIR CONCURRENT REQUIREMENTS None REFERENCES / REPERCUSSIONS TFU None OEB None AOT None SIL None LINE MAINTENANCE AFFECTED No LIFE LIMIT None OTHER OIT 999.0017/10 OIT 999.0071/10 OIT 999.0130/06 OIT 999.0067/12 AD 2014-0033 NATURE OF THE WORK AIRCRAFT YES EQUIPMENT NO HARD NO SOFT NO OBRM NO

DATE: Feb 07/13 SERVICE BULLETIN No.: A340-55-5007 REVISION No.: 01 - Aug 20/14 Page: 2 6

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# @A340-500/600 SERVICE BULLETIN SUMMARY MANPOWER Task 555007-832-848-001: Inspection TOTAL MANHOURS 38.00 APPENDICES None

DATE: Feb 07/13 SERVICE BULLETIN No.: A340-55-5007 REVISION No.: 01 - Aug 20/14 Page: 3 6

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# @A340-500/600 SERVICE BULLETIN SUMMARY
**CONF ALL
Z326 

### A

RUDDER SHELL TO BE INSPECTED 

### B



## A B LH SHOWN RH SHOWN F_SB_555007_6_SAAA_01_01 Figure A-GSAAA - Sheet 01
DATE: Feb 07/13 SERVICE BULLETIN No.: A340-55-5007 REVISION No.: 01 - Aug 20/14 Page: 4 6

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# @A340-500/600 SERVICE BULLETIN AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE Tel : (33) 5 61 93 33 33 Telex : AIRBU 530526F Fax : (33) 5 61 93 42 51



# MANDATORY MANDATORY MANDATORY ATA SYSTEM: 55 

### TITLE: STABILIZERS - RUDDER SIDE SHELL SANDWICH REPAIR INSPECTION 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 NOTE : This Service Bulletin is applicable to all rudders with the Serial Number (SN) from TS-5001 to TS-5138. NOTE : The related SRM procedures do currently not exist for A340-500/600 aircraft, but in case that repairs of rudder side shells which have been accomplished in accordance with a SRM A340-200/300 procedure older than SRM April 2010 revision, must be inspected in accordance with this Service Bulletin. NOTE : In the case of a rudder originally fitted on one aircraft (refer to AIR delivery document) that has been removed and installed on another aircraft, it is the responsibility of the operator to apply the required instructions contained in this Service Bulletin to the new aircraft. NOTE : In case of doubt, contact AIRBUS. (1) Models 340-541 340-542 340-642

DATE: Feb 07/13 SERVICE BULLETIN No.: A340-55-5007 REVISION No.: 01 - Aug 20/14 Page: 1 6

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# @A340-500/600 SERVICE BULLETIN (2) Effectivity by MSN 0371 0376 0383 0391 0394 0410 0416-0417 0426 0431 0436 0440 0445 0449 0453 0457 0460 0464 0468 0471 0475 0478 0482 0485 0488 0492 0495 0499 0514 0517 0520 0523 0531 0534 0537 0540 0543 0547 0557 0560 0563 0566 0569 0572 0575 0577 0580 0583 0586 0601 0604 0606 0608 0611 0615 0617 0619 0622 0624 0626 0628 0630 0639 0672 0677 0681 0685 0689 0694 0698 0702 0706 0710 0715 0719 0723 0727 0736 0740 0744 0748 0753 0757 0761-0768 0771 0775 0779 0783 0787 0790 0794 0798 0804 0812 0829 0837 0846 0848 0870 0897 0902 0910 0912 0917 0924 0929 0933 0953 0960 0972 0981 0987 0993 1005 1017 1030 1040 1079 1091 1122 (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 06U 1091 25R 0924 36V 0391 0416 70U 0902 72W 0917 AHY 0779 AIB 0478 0492 0499 0560 CES 0468 0488 0514 0577 0586 CHH 0436 0453 0475 DLH 0482 0517 0523 0537 0540 0543 0566 0569 0580 0583 0762 0763 0767 0771 0790 0794 0812 0846 0848 0897 0972 0981 0987 1005 ETD 0748 0757 0761 0783 0829 0837 0870 0929 0933 1030 1040 HFM 0383 HFY 0910 0912 IBE 0431 0440 0460 0601 0604 0606 0617 0619 0672 0702 0727 0744 0960 0993 1017 1079 1122 QAF 0495 QTR 0715 0740 0766 0798 SAA 0410 0417 0426 0531 0534 0547 0557 0626 0630 SIA 0563 TAM 0445 0464 THA 0624 0628 0677 0681 0689 0698 0710 0719 0775 0953 UAE 0394 0457 0471 0485 0520 0572 0608 0611 0685 0694 VIR 0371 0376 0449 0575 0615 0622 0639 0706 0723 0736 0753 0764 0765 0768 0787 0804

DATE: Feb 07/13 SERVICE BULLETIN No.: A340-55-5007 REVISION No.: 01 - Aug 20/14 Page: 2 6

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# @A340-500/600 SERVICE BULLETIN (4) Configuration by MSN MSN CONFIGURATION 0371 0376 0383 0391 0394 0410 0416 0417 0426 0431 0436 0440 0445 0449 0453 0457 0460 0464 0468 0471 0475 0478 0482 0485 0488 0492 0495 0499 0514 0517 0520 0523 0531 0534 0537 0540 0543 0547 0557 0560 0563 0566 0569 0572 0575 0577 0580 0583 0586 0601 0604 0606 0608 0611 0615 0617 0619 0622 0624 0626 0628 0630 0639 0672 0677 0681 0685 0689 0694 0698 0702 0706 0710 0715 0719 0723 0727 0736 0740 0744 0748 0753 0757 0761 0762 0763 0764 0765 0766 0767 0768 0771 0775 0779 0783 0787 0790 0794 0798 0804 0812 0829 0837 0846 0848 0870 0897 0902 0910 0912 0917 0924 0929 0933 0953 0960 0972 0981 0987 0993 1005 1017 1030 1040 1079 1091 1122 001

(5) Configuration definition **CONF 001 Config. 001 is valid for all the aircraft given in the effectivity of this Service Bulletin as a standard configuration. (6) Material Effectivity MATERIAL QTY PER A/C SEE NOTES Consumable CMLD01 1 B. CONCURRENT REQUIREMENTS None C. REASON (1) History On AIRBUS Single Aisle, Long Range and Wide Body family aircraft, the rudder side shell is a sandwich structure made of Carbon Fiber Reinforced Plastic (CFRP) and Glass Fiber Reinforced Plastic (GFRP) with a honeycomb core. A case of skin damage was reported on a composite side panel of a rudder installed on an A310 aircraft. Investigations have shown that the damage started from a skin panel area previously repaired in-service. This repair was performed as per A310 SRM 55-41-12 Fig. 204 procedure. The new damage has been identified as a damage between the core and the skin in the repaired area. This new damage has developed during normal operations due to the variation of pressure during ground-air-ground cycles. Following the above mentioned damage scenario, it has been identified that SRM procedures need to be improved to ensure an adequate repair quality. An improper bonding between skin and core during a repair may lead to a damage initiation and propagation, which may not be detectable visually. A large rudder damage, resulting from an undetected damage growth, could affect the handling quality of the aircraft.

DATE: Feb 07/13 SERVICE BULLETIN No.: A340-55-5007 REVISION No.: 01 - Aug 20/14 Page: 3 6

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# @A340-500/600 SERVICE BULLETIN (2) Objective/Action This Service Bulletin details the inspection procedure to inspect affected rudders fitted on A340 aircraft for potential damage. Different inspection procedures are necessary: - Pulse thermography inspection - Elasticity Laminate Checker (ELCH) inspection - Ultrasonic Testing (UT) inspection. - Tap test inspection. (3) Advantages The accomplishment of this Service Bulletin will contribute to detect potential damage around in-service repairs accomplished on rudders made of Carbon Fiber Reinforced Plastic (CFRP) and Glass Fiber Reinforced Plastic (GFRP) with a honeycomb core. (4) Operational/Maintenance Consequences None D. DESCRIPTION NOTE : The listed subtasks are not in sequence with the work steps. To accomplish this Service Bulletin it is necessary to : Task 555007-832-848-001: Inspection (1) Check the rudder repair records (2) Identify the type, location and size of in-service repairs on the rudder side shell CFRP areas in case of complete repair records since rudder Entry Into Service (EIS) are available (3) Do a pulse thermography inspection on the complete rudder side shell CFRP areas to identify possible rudder in-service repairs in case of repair records are not complete or not available (4) Do the corrective actions in case of fluid ingress detected (5) Do the ELCH and/or UT inspection around identified repairs/fluid ingress (6) Do terminating actions in case of no damage detected (7) Inspect the rudder side shell upper GFRP areas (8) Close the holes in case of drilling thru the outer skin during paint thickness measurement DATE: Feb 07/13 SERVICE BULLETIN No.: A340-55-5007 REVISION No.: 01 - Aug 20/14 Page: 4 6

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# @A340-500/600 SERVICE BULLETIN (9) Identify the repair size by local sanding E. COMPLIANCE (1) Classification MANDATORY: Service Bulletin must be accomplished. (2) Accomplishment Timescale This Service Bulletin has been classified Mandatory by the issue of an Airworthiness Directive (AD) published by the European Aviation Safety Agency (EASA). The AD must be used as the reference document for the mandated accomplishment timescale. Table 1, Config. 001 - Rudder special detailed inspection for repair detection Condition Action Compliance time Repetitive interval All aircraft Identify the Serial Number of the installed rudder in accordance with the accomplishment instructions Subtask 555007-832-201-001 Within 4 months from original Service Bulletin issue date None

All aircraft Check the completeness of the rudder repair records Within 4 months from original Service Bulletin issue date None All aircraft Report information about the repair records to AIRBUS Within 4 months from original Service Bulletin issue date None Repair records are not complete or not available Continue with the actions given in table 2A for CFRP areas Refer to table 2A Refer to table 2A Repair records are not complete or not available Continue with the actions given in table 2B for GFRP areas Refer to table 2B Refer to table 2B Complete repair records since rudder Entry Into Service (EIS) are available Continue with the actions given in table 2C for CFRP areas Refer to table 2C Refer to table 2C Complete repair records since rudder EIS are available Continue with the actions given in table 2D for GFRP areas Refer to table 2D Refer to table 2D Table 2A, Config. 001 - Repair records are not complete or not available (CFRP areas) Condition Action Compliance time Repetitive interval Repair records are not complete or not available Report undocumented rudder Serial Number list to AIRBUS to get related rudder manufacturing rework data 3 months in advance before pulse thermography inspection is scheduled None

DATE: Feb 07/13 SERVICE BULLETIN No.: A340-55-5007 REVISION No.: 01 - Aug 20/14 Page: 5 6

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# @A340-500/600 SERVICE BULLETIN Table 2A, Config. 001 - Repair records are not complete or not available (CFRP areas) Condition Action Compliance time Repetitive interval Repair records are not complete or not available Make sure that the paint thickness in all areas to be inspected does not exceed the limits given in the accomplishment instructions Subtask 555007-832-203-001 Within 24 months from original Service Bulletin issue date, before the pulse thermography inspection None

Repair records are not complete or not available Do a pulse thermography inspection on the complete side shells (LH/RH) to identify repairs in accordance with the accomplishment instructions Subtask 555007-832-203-001 Within 24 months from original Service Bulletin issue date None

No repair detected Report to AIRBUS No further action necessary in accordance with this Service Bulletin Within 1 month from the pulse thermography inspection None
Repairs in the booster area =< 55000 mm 2 (85.25 sq.in.) detected Report to AIRBUS Within 1 month from the pulse thermography inspection None Repairs in the booster area > 55000 mm 2 (85.25 sq.in.) or not in the booster area detected during pulse thermography inspection Do an ELCH and/or UT inspection around the identified repairs in accordance with the accomplishment instructions Subtask 555007-832-205-001 Within 24 months from original Service Bulletin issue date None

Fluid ingress detected during pulse thermography/UT inspection Continue with the actions given in table 3 Refer to table 3 Refer to table 3
Damage detected during ELCH and/or UT inspection Provide a detailed damage report and report to AIRBUS and follow their instructions Before next flight None No damage detected during ELCH and/or UT inspection Continue with the actions given in table 4 Refer to table 4 Refer to table 4

DATE: Feb 07/13 SERVICE BULLETIN No.: A340-55-5007 REVISION No.: 01 - Aug 20/14 Page: 6 6

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# @A340-500/600 SERVICE BULLETIN Table 2B, Config. 001 - Repair records are not complete or not available (GFRP areas) Condition Action Compliance time Repetitive interval Repair records are not complete or not available Make sure that the paint thickness in all areas to be inspected does not exceed the limits given in the accomplishment instructions 555007-832-207-001 Within 24 months from original Service Bulletin issue date, before the pulse thermography inspection None

Repair records are not complete or not available Do a pulse thermography inspection on the complete GFRP area in accordance with the accomplishment instructions Subtask 555007-832-207-001 Within 24 months from original Service Bulletin issue date None

Repair records are not complete or not available In case of findings, mark the repairs which are not manufacturing reworks Within 24 months from original Service Bulletin issue date None Repair records are not complete or not available Do a Tap test inspection on the complete GFRP area to identify skin to core disbonding in accordance with the accomplishment instructions Subtask 555007-832-207-001 Within 24 months from original Service Bulletin issue date None

No skin to core disbonding but repairs identified Do an ELCH and/or UT inspection on the complete GFRP area in accordance with the accomplishment instructions Subtask 555007-832-205-001 Within 24 months from original Service Bulletin issue date None

Fluid ingress detected during pulse thermography/UT inspection Continue with the actions given in table 3 Refer to table 3 Refer to table 3
Damage detected during tap test/ELCH and/or UT inspection Provide a detailed damage report and report to AIRBUS and follow their instructions Before next flight None No damage detected during tap test/ELCH and/or UT inspection Continue with the actions given in table 4 Refer to table 4 Refer to table 4

DATE: Feb 07/13 SERVICE BULLETIN No.: A340-55-5007 REVISION No.: 01 - Aug 20/14 Page: 7 6

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# @A340-500/600 SERVICE BULLETIN Table 2C, Config. 001 - Repair records since rudder EIS are complete (CFRP areas) Condition Action Compliance time Repetitive interval No repair performed or repair not to be inspected in accordance with this Service Bulletin Report to AIRBUS No further action necessary in accordance with this Service Bulletin Within 24 months from original Service Bulletin issue date None
Repair is performed since rudder EIS Identify the repair type in accordance with the accomplishment instructions Subtask 555007-832-202-001 Within 24 months from original Service Bulletin issue date None
Repair identified as type to be inspected Make sure that the paint thickness in all areas to be inspected does not exceed the limits given in the accomplishment instructions Subtask 555007-832-202-001 Within 24 months from original Service Bulletin issue date, before the pulse thermography inspection None

Repair identified as type to be inspected Do a pulse thermography inspection on repair location in accordance with the accomplishment instructions Subtask 555007-832-202-001 or Identify the repair size by local sanding, refer to Subtask 555007-832-208-001 Within 24 months from original Service Bulletin issue date None

Repairs in the booster area =< 55000 mm 2 (85.25 sq.in.) detected during pulse thermography inspection or local sanding Report to AIRBUS Within 1 month from pulse thermography inspection None

Repairs in the booster area > 55000 mm 2 (85.25 sq.in.) or not in the booster area detected during pulse thermography inspection or local sanding Do an ELCH and/or UT inspection around the identified repairs in accordance with the accomplishment instructions Subtask 555007-832-205-001 Within 24 months from original Service Bulletin issue date None

Fluid ingress detected during pulse thermography/UT inspection Continue with the actions given in table 3 Refer to table 3 Refer to table 3

DATE: Feb 07/13 SERVICE BULLETIN No.: A340-55-5007 REVISION No.: 01 - Aug 20/14 Page: 8 6

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# @A340-500/600 SERVICE BULLETIN Table 2C, Config. 001 - Repair records since rudder EIS are complete (CFRP areas) Condition Action Compliance time Repetitive interval Damage detected during ELCH and/or UT inspection Provide a detailed damage report, report to AIRBUS and follow their instructions Before next flight None No damage detected during ELCH and/or UT inspection Continue with the actions given in table 4 Refer to table 4 Refer to table 4
Table 2D, Config. 001 - Repair records since rudder EIS are complete (GFRP areas) Condition Action Compliance time Repetitive interval No repair performed or repair not to be inspected in accordance with this Service Bulletin Report to AIRBUS No further action necessary in accordance with this Service Bulletin Within 24 months from original Service Bulletin issue date None
Repair performed and identified as type to be inspected Make sure that the paint thickness in all areas to be inspected does not exceed the limits given in the accomplishment instructions Subtask 555007-832-207-001 Within 24 months from original Service Bulletin issue date, before the pulse thermography inspection None

Repair identified as type to be inspected Do a pulse thermography inspection on repair location in accordance with the accomplishment instructions Subtask 555007-832-207-001 or Identify the repair size by local sanding, refer to Subtask 555007-832-208-001 Within 24 months from original Service Bulletin issue date None

Repair type A-A identified Do a Tap test inspection on the repair in accordance with the accomplishment instructions Subtask 555007-832-207-001 Within 24 months from original Service Bulletin issue date None

All other repairs Do an ELCH and/or UT inspection around the identified repairs in accordance with the accomplishment instructions Subtask 555007-832-205-001 Within 24 months from original Service Bulletin issue date None

DATE: Feb 07/13 SERVICE BULLETIN No.: A340-55-5007 REVISION No.: 01 - Aug 20/14 Page: 9 6

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# @A340-500/600 SERVICE BULLETIN Table 2D, Config. 001 - Repair records since rudder EIS are complete (GFRP areas) Condition Action Compliance time Repetitive interval Fluid ingress detected during pulse thermography/UT inspection Continue with the actions given in table 3 Refer to table 3 Refer to table 3
Damage detected during tap test/ELCH and/or UT inspection Provide a detailed damage report and report to AIRBUS and follow their instructions Before next flight None No damage detected during tap test/ELCH and/or UT inspection Continue with the actions given in table 4 Refer to table 4 Refer to table 4
Table 3, Config. 001 - Fluid ingress detected Condition Action Compliance time Repetitive interval Fluid ingress detected Do an ELCH and/or UT inspection around the identified fluid ingress in accordance with the accomplishment instructions Subtask 555007-832-205-001 Before next flight None

Damage detected around the identified fluid ingress Report to AIRBUS and follow their instructions Before next flight None Local single spot fluid ingress =< 1500 mm 2 (2.33 sq.in.) detected (no damage detected around the identified fluid ingress) Report to AIRBUS Within 1 month from pulse thermography inspection None

Maximum of 5 local single spots fluid ingress per side shell > 1500 mm 2 (2.33 sq.in.) and =< 5000 mm 2 (7.75 sq.in.) detected (no damage detected around the identified fluid ingress) Drain by core ventilation in accordance with the accomplishment instructions Subtask 555007-832-204-001 Before next flight None

Core ventilation done Option 1: Close the holes with adhesive tape Before next flight None Holes closed with tape Option 1: Do repetitive detailed inspections of the restored area for loose or lost tape Within 900 FH after closing the holes At intervals not exceeding 900 FH

DATE: Feb 07/13 SERVICE BULLETIN No.: A340-55-5007 REVISION No.: 01 - Aug 20/14 Page: 10 6

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# @A340-500/600 SERVICE BULLETIN Table 3, Config. 001 - Fluid ingress detected Condition Action Compliance time Repetitive interval Loose or lost tape found Option 1: Close the holes again with adhesive tape or refer to Option 2 Before next flight None

Core ventilation done Option 2: Close the holes with GFRP plies Before next flight None Maximum of 5 local single spots fluid ingress per side shell > 1500 mm 2 (2.33 sq.in.) and =< 5000 mm 2 (7.75 sq.in.) detected (no damage detected around the identified fluid ingress) Option 1 and 2: Repetitive thermography inspections in accordance with the accomplishment instructions Subtask 555007-832-204-001 Within 1000 FC after closing the holes Within intervals of 1000 FC until repair

Maximum of 5 local single spots fluid ingress per side shell > 1500 mm 2 (2.33 sq.in.) and =< 5000 mm 2 (7.75 sq.in.) detected (no damage detected around the identified fluid ingress) Do the repair Within 4500 FC, but not exceeding 24 months from the first inspection None

Maximum of 5 local single spots fluid ingress per side shell > 1500 mm 2 (2.33 sq.in.) and =< 5000 mm 2 (7.75 sq.in.) detected (no damage detected around the identified fluid ingress) Report to AIRBUS Within 1 month from the repair None

More than 5 local single spots fluid ingress per side shell > 1500 mm 2 (2.33 sq.in.) and =< 5000 mm 2 (7.75 sq.in.) detected (no damage detected around the identified fluid ingress) Report to AIRBUS and follow their instructions Before next flight None

Local single spot fluid ingress > 5000 mm 2 (7.75 sq.in.) detected (no damage detected around the identified fluid ingress) Report to AIRBUS and follow their instructions Before next flight None

Tables 4.A thru 4.D, Config. 001: No damage detected during ELCH/UT inspection:
DATE: Feb 07/13 SERVICE BULLETIN No.: A340-55-5007 REVISION No.: 01 - Aug 20/14 Page: 11 6

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# @A340-500/600 SERVICE BULLETIN For an identified repair size of a maximum of 10000 mm 2 (15.50 sq.in.), continue with table 4.A. For an identified repair size larger than 10000 mm 2 (15.50 sq.in.) and up to 20000 mm 2 (31.00 sq.in.), continue with table 4.B. For an identified repair size larger than 20000 mm 2 (31.00 sq.in.) and up to 80000 mm 2 (124 sq.in.), continue with table 4.C. For an identified repair size larger than 80000 mm 2 (124 sq.in.), continue with table 4.D. Table 4.A, Config. 001 - Identified repair size of a maximum of 10000 mm 2 (15.50 sq.in.) Condition Action Compliance time Repetitive interval Repair size =< 10000 mm 2 (15.50 sq.in.) Provide detailed information about the identified repair and report to AIRBUS Within 1 month from ELCH/UT inspection None
Table 4.B, Config. 001 - Identified repair size larger than 10000 mm 2 (15.50 sq.in.) and up to 20000 mm 2(31.00 sq.in.) Condition Action Compliance time Repetitive interval Repair size > 10000 mm 2 (15.50 sq.in.) and =< 20000 mm 2 (31.00 sq.in.) Option 1: Do the core ventilation thru the inner skin in accordance with the accomplishment instructions Subtask 555007-832-206-001 Before next flight None

Core ventilation done Option 1: Hole closing option 1: Close the holes with adhesive tape Before next flight None
Holes closed with tape Option 1: Hole closing option 1: Do repetitive detailed inspections of the restored area for loose or lost tape Within 900 FH after closing the holes At intervals not exceeding 900 FH
Loose or lost tape found Option 1: Hole closing option 1: Close the holes again with adhesive tape or refer to hole closing option 2 Before next flight None

Core ventilation done Option 1: Hole closing option 2: Close the holes with GFRP plies Before next flight None

DATE: Feb 07/13 SERVICE BULLETIN No.: A340-55-5007 REVISION No.: 01 - Aug 20/14 Page: 12 6

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# @A340-500/600 SERVICE BULLETIN Table 4.B, Config. 001 - Identified repair size larger than 10000 mm 2 (15.50 sq.in.) and up to 20000 mm 2(31.00 sq.in.) Condition Action Compliance time Repetitive interval Core ventilation done Option 1: Report detailed information about the identified repair and the planned terminating action to AIRBUS Within 1 month from first ELCH/UT inspection None

Core ventilation done Option 1: Do the repair in accordance with the SRM at the identified repair location Within 4500 FC, not exceeding 24 months, from the first inspection date None
Repair size > 10000 mm 2 (15.50 sq.in.) and =< 20000 mm 2 (31.00 sq.in.) Option 2: Do repetitive ELCH/UT inspections around the identified repair area in accordance with the accomplishment instructions Subtask 555007-832-205-001 Within 900 FH from first ELCH/UT inspection Every 900 FH from last ELCH/UT inspection

Findings during repetitive ELCH/UT inspections Option 2: Report to AIRBUS and follow their instructions Before next flight None No findings during repetitive ELCH/UT inspections Option 2: Report detailed information about the identified repair and the planned terminating action to AIRBUS Within 1 month from ELCH/UT inspection None

No findings during repetitive ELCH/UT inspections Option 2: Do the repair in accordance with the SRM at the identified repair location Within 4500 FC, not exceeding 24 months, from the first inspection date None

Table 4.C, Config. 001 - Identified repair size larger than 20000 mm 2 (31.00 sq.in.) and up to 80000 mm 2 (124 sq.in.) Condition Action Compliance time Repetitive interval Repair size > 20000 mm 2 (31.00 sq.in.) and =< 80000 mm 2 (124 sq.in.) Do the core ventilation thru inner skin in accordance with the accomplishment instructions Subtask 555007-832-206-001 Before next flight None

Core ventilation done Option 1: Close the holes with adhesive tape Before next flight None

DATE: Feb 07/13 SERVICE BULLETIN No.: A340-55-5007 REVISION No.: 01 - Aug 20/14 Page: 13 6

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# @A340-500/600 SERVICE BULLETIN Table 4.C, Config. 001 - Identified repair size larger than 20000 mm 2 (31.00 sq.in.) and up to 80000 mm 2 (124 sq.in.) Condition Action Compliance time Repetitive interval Holes closed with tape Option 1: Do repetitive detailed inspections of the restored area for loose or lost tape Within 900 FH after closing the holes At intervals not exceeding 900 FH
Loose or lost tape found Option 1: Close the holes again with adhesive tape or refer to Option 2 Before next flight None

Core ventilation done Option 2: Close the holes with GFRP plies Before next flight None Repair size > 20000 mm 2 (31.00 sq.in.) and =< 80000 mm 2 (124 sq.in.) Report detailed information about the identified repair and the planned terminating action to AIRBUS Within 1 month from first ELCH/UT inspection None

Core ventilation done and repair size =< 30000 mm 2 (46.50 sq.in.) Do the repair in accordance with the SRM at the identified repair location Within 4500 FC, not exceeding 24 months, from the first inspection date None

Core ventilation done and repair size > 30000 mm 2 (46.50 sq.in.) and =< 80000 mm 2 (124 sq.in.) Do the repair in accordance with the SRM and additional instructions from AIRBUS Within 4500 FC, not exceeding 24 months, from the first inspection date None

Table 4.D, Config. 001 - Identified repair size larger than 80000 mm 2 (124 sq.in.) Condition Action Compliance time Repetitive interval Repair size > 80000 mm 2 (124 sq.in.) Do the core ventilation thru inner skin in accordance with the accomplishment instructions Subtask 555007-832-206-001 Before next flight None

Core ventilation done Option 1: Close the holes with adhesive tape Before next flight None Holes closed with tape Option 1: Do repetitive detailed inspections of the restored area for loose or lost tape Within 900 FH after closing the holes At intervals not exceeding 900 FH

DATE: Feb 07/13 SERVICE BULLETIN No.: A340-55-5007 REVISION No.: 01 - Aug 20/14 Page: 14 6

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# @A340-500/600 SERVICE BULLETIN Table 4.D, Config. 001 - Identified repair size larger than 80000 mm 2 (124 sq.in.) Condition Action Compliance time Repetitive interval Loose or lost tape found Option 1: Close the holes again with adhesive tape or refer to Option 2 Before next flight None

Core ventilation done Option 2: Close the holes with GFRP plies Before next flight None Repair size > 80000 mm 2 (124 sq.in.) Report detailed information about the identified repair and the planned terminating action to AIRBUS Within 1 month from first ELCH/UT inspection None
Repair size > 80000 mm 2 (124 sq.in.) Replace the affected rudder shell OR Replace the rudder No further action necessary in accordance with this Service Bulletin Within 4500 FC, not exceeding 24 months, from the first inspection date None

Table 5, Config. 001 - Hole closing in case of damaged outer skin during paint thickness measurement Condition Action Compliance time Repetitive interval Sandwich structure damaged Option 1: Close the holes with resin and adhesive tape Before next flight None Holes closed Option 1: Restore the surface protection Within 4500 FC from the pulse thermography inspection None Sandwich structure damaged Option 2: Do the permanent restoration procedure Before next flight None
Table 6.A, Config. 001 - Identify the repair size by local sanding Condition Action Compliance time Repetitive interval Repair performed and identified as type to be inspected Identify paint thickness and primer Within 24 months from original Service Bulletin issue date None Repair performed and identified as type to be inspected Do local sanding on top and around the repair up to the initial basic primer Within 24 months from original Service Bulletin issue date None
Largest repair ply is not visible Continue with the actions given in table 6.B Before next flight None

DATE: Feb 07/13 SERVICE BULLETIN No.: A340-55-5007 REVISION No.: 01 - Aug 20/14 Page: 15 6

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# @A340-500/600 SERVICE BULLETIN Table 6.A, Config. 001 - Identify the repair size by local sanding Condition Action Compliance time Repetitive interval Largest repair ply is visible Remove the dust and dry the area Before next flight None Largest repair ply is visible Inspect the sanded area for damage Before next flight None Damage found Do the damage assessment Before next flight None No damage found Mark the repair on the rudder surface Before next flight None Repairs in the booster area =< 55000 mm 2 (85.25 sq.in.) detected Restore the surface protection Before next flight None Repairs in the booster area =< 55000 mm 2 (85.25 sq.in.) detected Report to AIRBUS Within 1 month None Repairs in the booster area > 55000 mm 2 (85.25 sq.in.) or not in the booster area detected Do an ELCH and/or UT inspection around the identified repairs in accordance with the accomplishment instructions Subtask 555007-832-205-001 Before next flight None

Fluid ingress detected during UT inspection Continue with the actions given in table 3 Refer to table 3 Refer to table 3 Damage detected during ELCH and/or UT inspection Provide a detailed damage report, report to AIRBUS and follow their instructions Before next flight None No damage detected during ELCH and/or UT inspection Continue with the actions given in table 4 Refer to table 4 Refer to table 4
Table 6.B, Config. 001 - Identify the repair size by local sanding - largest repair ply not visible Condition Action Compliance time Repetitive interval Largest repair ply is not visible Continue local sanding up to the pore filler/adhesive Before next flight None Largest repair ply is visible now Remove the dust and dry the area Before next flight None Largest repair ply is still not visible Continue with the actions given in table 6.C for CFRP areas and table 6.D for GFRP areas Before next flight None
Largest repair ply is visible now Inspect the sanded area for damage Before next flight None

DATE: Feb 07/13 SERVICE BULLETIN No.: A340-55-5007 REVISION No.: 01 - Aug 20/14 Page: 16 6

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# @A340-500/600 SERVICE BULLETIN Table 6.B, Config. 001 - Identify the repair size by local sanding - largest repair ply not visible Condition Action Compliance time Repetitive interval Damage found Do the damage assessment Before next flight None No damage found Mark the repair on the rudder surface Before next flight None Repairs in the booster area =< 55000 mm 2 (85.25 sq.in.) detected Restore the surface protection Before next flight None Repairs in the booster area =< 55000 mm 2 (85.25 sq.in.) detected Report to AIRBUS Within 1 month None Repairs in the booster area > 55000 mm 2 (85.25 sq.in.) or not in the booster area detected Do an ELCH and/or UT inspection around the identified repairs in accordance with the accomplishment instructions Subtask 555007-832-205-001 Before next flight None

Fluid ingress detected during UT inspection Continue with the actions given in table 3 Refer to table 3 Refer to table 3 Damage detected during ELCH and/or UT inspection Provide a detailed damage report, report to AIRBUS and follow their instructions Before next flight None No damage detected during ELCH and/or UT inspection Continue with the actions given in table 4 Refer to table 4 Refer to table 4
Table 6.C, Config. 001 - Do the pulse thermography inspection (CFRP areas) Condition Action Compliance time Repetitive interval Largest repair ply is still not visible Do a pulse thermography inspection on repair location in accordance with the accomplishment instructions Subtask 555007-832-202-001 Before next flight None

Repairs in the booster area =< 55000 mm 2 (85.25 sq.in.) detected during pulse thermography inspection Restore the surface protection Before next flight None
Repairs in the booster area =< 55000 mm 2 (85.25 sq.in.) detected during pulse thermography inspection Report to AIRBUS Within 1 month None

DATE: Feb 07/13 SERVICE BULLETIN No.: A340-55-5007 REVISION No.: 01 - Aug 20/14 Page: 17 6

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# @A340-500/600 SERVICE BULLETIN Table 6.C, Config. 001 - Do the pulse thermography inspection (CFRP areas) Condition Action Compliance time Repetitive interval Repairs in the booster area > 55000 mm 2 (85.25 sq.in.) or not in the booster area detected during pulse thermography inspection Do an ELCH and/or UT inspection around the identified repairs in accordance with the accomplishment instructions Subtask 555007-832-205-001 Before next flight None

Fluid ingress detected during pulse thermography/UT inspection Continue with the actions given in table 3 Refer to table 3 Refer to table 3
Damage detected during ELCH and/or UT inspection Provide a detailed damage report, report to AIRBUS and follow their instructions Before next flight None No damage detected during ELCH and/or UT inspection Continue with the actions given in table 4 Refer to table 4 Refer to table 4
Table 6.D, Config. 001 - Do the pulse thermography inspection (GFRP areas) Condition Action Compliance time Repetitive interval Repair identified as type to be inspected Do a pulse thermography inspection on repair location in accordance with the accomplishment instructions Subtask 555007-832-207-001 Before next flight None

Repair type A-A identified Do a Tap test inspection on the identified repair in accordance with the accomplishment instructions Subtask 555007-832-207-001 Before next flight None

All other repairs Do an ELCH and/or UT inspection around the identified repairs in accordance with the accomplishment instructions Subtask 555007-832-205-001 Before next flight None

Fluid ingress detected during pulse thermography/UT inspection Continue with the actions given in table 3 Refer to table 3 Refer to table 3

DATE: Feb 07/13 SERVICE BULLETIN No.: A340-55-5007 REVISION No.: 01 - Aug 20/14 Page: 18 6

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# @A340-500/600 SERVICE BULLETIN Damage detected during Tap test/ELCH and/or UT inspection Provide a detailed damage report, report to AIRBUS and follow their instructions Before next flight None No damage detected during ELCH and/or UT inspection Continue with the actions given in table 4 Refer to table 4 Refer to table 4
F. APPROVAL The technical content of this document is approved under authority of Design Organization Approval No . EASA.21J.031. If an aircraft listed in the effectivity has a modification or repair embodied that is not of AIRBUS origin, and which affects the content of this Service Bulletin, the operator is responsible for obtaining approval by its airworthiness authority for any adaptation necessary before incorporation of the Service Bulletin. 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. Task 555007-832-848-001: Inspection Get Access 1.00 On Aircraft Check the rudder repair records 4.00 Identify the type, location and size of in-service repairs on the rudder side shell CFRP areas in case of complete repair records since rudder Entry Into Service (EIS) are available 0
Do a pulse thermography inspection on the complete rudder side shell CFRP areas to identify possible rudder in-service repairs in case of repair records are not complete or not available 32.00
Do the corrective actions in case of fluid ingress detected 0 Do the ELCH and/or UT inspection around identified repairs/fluid ingress 0 Do terminating actions in case of no damage detected 0 Inspect the rudder side shell upper GFRP areas 0 Close the holes in case of drilling thru the outer skin during paint thickness measurement 0 Identify the repair size by local sanding 0 Close-Up 1.00 TOTAL MANHOURS 38.00 DATE: Feb 07/13 SERVICE BULLETIN No.: A340-55-5007 REVISION No.: 01 - Aug 20/14 Page: 19 6

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# @A340-500/600 SERVICE BULLETIN NOTE : Manhours and elapsed time depend on the size of the area to be inspected. Find below a table with the information for the manhours, elapsed time and number of persons per 1 m 2 (1550 sq.in.) for the different inspection procedures: Steps Manhours Elapsed time Number of persons Get access 1.00 0.75 2 Rudder SN identification 0.25 0.25 1 Pulse thermography inspection 1.00 0.50 2 UT inspection 1.25 1.25 1 ELCH inspection 1.50 0.75 1 Tap test inspection 0.25 0.25 1 Local sanding 1.00 1.00 1 Close-up 1.00 0.75 2 H. WEIGHT AND BALANCE Not Changed I. ELECTRICAL LOAD DATA Not Changed J. REFERENCES

Aircraft Maintenance Manual (AMM) 06-41-55 12-34-24 20-16-00 29-00-00 55-40-00 Consumable Material List (CML) Elec. Std. Practices Manual (ESPM) 20-55-00 Non Destructive Test Manual (NTM) 51-10-03 51-10-19 51-10-24 51-10-25 51-10-26 55-40-09 55-40-50 Structural Repair Manual (SRM) 51-23-11 51-75-11 51-75-12 51-77-10 51-77-11 K. PUBLICATION AFFECTED None L. INTERCHANGEABILITY/MIXABILITY Not Applicable M. SPARES None
DATE: Feb 07/13 SERVICE BULLETIN No.: A340-55-5007 REVISION No.: 01 - Aug 20/14 Page: 20 6

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# @A340-500/600 SERVICE BULLETIN 2. MATERIAL INFORMATION **CONF ALL A. MATERIAL - PRICE AND AVAILABILITY (1) Procurement Addresses None This Service Bulletin is the subject of an AIRBUS monitored retrofit campaign. (2) Price and Availability None B. INDUSTRY SUPPORT INFORMATION For the organisation of this retrofit, you are kindly requested to contact AIRBUS retrofit management department: AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX France E-mail : monitored.retrofit@airbus.com Tel : (33) 5 67 19 06 22 Fax : (33) 5 61 93 27 45 AIRBUS will provide specific industry support for inspection Service Bulletin completion. For detailed information, please contact your AIRBUS Customer Support Director. C. LIST OF COMPONENTS No Kit D. LIST OF MATERIALS - OPERATOR SUPPLIED (1) Consumable Materials Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Adhesive Film Tape- Aluminium Foil 05RAB9 As required Pressure Sensitive Tape 05RFB1 As required Self-Adhes. Disks 05TNB1 As required Non Aqueous Cleaner-General 08BAA9 As required Methyl-Ethyl-Ketone 08BBF1 As required Trichloroethane Legacy 08BBU9 As required
DATE: Feb 07/13 SERVICE BULLETIN No.: A340-55-5007 REVISION No.: 01 - Aug 20/14 Page: 21 6

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# @A340-500/600 SERVICE BULLETIN
ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Laminating Resin-Epoxy Srm Type 2 - 13EBC1 As required Textile-Lint Free Cotton 14SBA1 As required (2) Components None (3) Equipment None E. PARTS TO BE RE-IDENTIFIED BY OPERATOR None F. TOOLING (1) Tooling - Price and Availability Not Applicable (2) Tools To find the correct tool-PN for the different inspection tools, refer to the subsequent table: Inspection tool PN UT inspection UT-equipment Refer to NTM 51-10-24 Tap test inspection Tap test inspection tool Refer to NTM 51-10-03 Tap test inspection (with Woodpecker) Function test block and Woodpecker Refer to NTM 51-10-19 ELCH inspection Elasticity Laminate Checker Kit Refer to NTM 51-10-26 Pulse thermography inspection Pulse thermography kit 99A55407324000 Thermography inspection Thermography kit Refer to NTM 51-10-25 Paint thickness measurement Paint Borer Kit Model 518 or 518S or 518MC with drill measuring range 10 to 1000 and 20 to 2000 microns To order the pulse thermography kit and the paint borer kit, contact: For tools on loan: AIRBUS Material, Logistics and Suppliers Lease Tool Service Weg beim Jaeger 150 D-22335 HAMBURG Germany DATE: Feb 07/13 SERVICE BULLETIN No.: A340-55-5007 REVISION No.: 01 - Aug 20/14 Page: 22 6

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# @A340-500/600 SERVICE BULLETIN For ordering by internet : http.//spares.airbus.com For ordering by E-mail: tool.lease@airbus.com For ordering by fax: +49 40 5076 3225 For tools to buy: AIRBUS Material, Logistics and Suppliers IFD- In Flight Desk Weg beim Jaeger 150 D-22335 HAMBURG Germany For ordering by internet : http.//spares.airbus.com For ordering by E-mail: ifd.spares@airbus.com For ordering by fax: +49 40 5076 4012 (3) Special Tools None

DATE: Feb 07/13 SERVICE BULLETIN No.: A340-55-5007 REVISION No.: 01 - Aug 20/14 Page: 23 6

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# @A340-500/600 SERVICE BULLETIN

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# @A340-500/600 SERVICE BULLETIN 3. ACCOMPLISHMENT INSTRUCTIONS Task 555007-832-848-001 - Inspection WARNING : MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS INCLUDED IN THE REFERENCED PROCEDURES. WARNING : OBEY THE MANUFACTURERS INSTRUCTIONS WHEN YOU USE CLEANING AGENTS, ADHESIVES, SEALANTS AND PAINTS. THESE MATERIALS ARE DANGEROUS. WARNING : WEAR THE CORRECT PROTECTIVE GLOVES, GOGGLES AND FILTER MASKS WHEN YOU USE CLEANING AGENTS, ADHESIVES, SEALANTS AND PAINTS. THESE MATERIALS ARE DANGEROUS. CAUTION : ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP ELECTRICAL WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY AND MECHANICALLY SERVICEABLE) . WHEN YOU DO MAINTENANCE WORK, REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING, COMPONENTS AND THE WORK AREA AS CLEAN AS POSSIBLE. TO DO THIS: PUT PROTECTION, SUCH AS PLASTIC SHEETING, CLOTHS, ETC; AS NECESSARY ON WIRING AND COMPONENTS. REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND OTHER CONTAMINATION. THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION AND DAMAGE TO THE ELECTRICAL WIRING INSTALLATION. IN CASE OF CONTAMINATION REFER TO ESPM 20-55-00. NOTE : The accomplishment instructions of this Service Bulletin refer to procedures included in other AIRBUS documents. When the words ’refer to’ are used and the operator has an accepted alternative procedure, the accepted alternative procedure can be used. When the words ’in accordance with’ are included in the instruction, the procedure in the AIRBUS document must be used. NOTE : The access and close-up instructions, not comprising return to service tests, in this Service Bulletin do not constitute or affect the technical intent of the Service Bulletin. Operators can therefore, as deemed necessary, omit or add access and/or close-up steps to add flexibility to their maintenance operations as long as the technical intent of the Service Bulletin is met within the set parameters. NOTE : Manual titles given in the accomplishment instructions are referred to by acronyms. Refer to paragraph 1.J., References, for the definition of acronyms. NOTE : The purpose of flow charts is to supplement the information given in the Procedure and Compliance paragraphs and not to serve as the primary source for tasks or compliance times given in this Service Bulletin. NOTE : This Service Bulletin is classified mandatory or expected to be classified mandatory

DATE: Feb 07/13 SERVICE BULLETIN No.: A340-55-5007 REVISION No.: 01 - Aug 20/14 Page: 25 6

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# @A340-500/600 SERVICE BULLETIN by an Airworthiness Directive (AD). The paragraphs 3.C. and 3.D. in these accomplishment instructions are Required for Compliance (RC) and must be done to comply with the AD. Other paragraphs are recommended and may be deviated from, done as part of other actions or done with accepted methods different from those given in the Service Bulletin, as long as the RC paragraphs can be done and the aircraft can be put back into a serviceable condition. Task Associated Data Manpower TOTAL MANHOURS 38.00 A. GENERAL (1) Subtask 555007-910-201-001 - Standard Practices Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-41-55, Page Block 001 Task 20-16-00-912-801 Consumable Material List (CML) (a) For location of the access panels refer to AMM 06-41-55, Page Block 001. (b) For the specification of consumable materials (Mat. No.) given in this Service Bulletin refer to Consumable Material List (CML). (c) For circuit breaker safety practices refer to AMM Task 20-16-00-912-801. (d) The purpose of flow charts are for information only to show the vario/Repair phases described in this Service Bulletin. (2) Subtask 555007-839-201-001 - Administrative Manpower Resources Skills NON SPECIFIC Write in the applicable aircraft records that you have done all the work given in this Service Bulletin. B. PREPARATION (1) Subtask 555007-941-201-001 - Job Set-up Manpower Resources Skills NON SPECIFIC

DATE: Feb 07/13 SERVICE BULLETIN No.: A340-55-5007 REVISION No.: 01 - Aug 20/14 Page: 26 6

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# @A340-500/600 SERVICE BULLETIN
References Aircraft Maintenance Manual (AMM) Task 12-34-24-860-802 Task 29-00-00-864-801 Task 29-00-00-864-802 Task 29-00-00-864-803 55-40-00, Page Block 601 NOTE : The items given in this note shall be considered as the basic Aircraft configuration before you start a maintenance task: - Aircraft on the ground resting on landing gear (the ground safety locks and the wheel chocks are in position on the landing gear). - Engine shut down, thrust reversers closed and locked. - Aircraft in clean configuration. - Parking brake applied. - Aircraft electrical network de-energized. - Hydraulic systems depressurized. - Access to the cockpit and cabin is available. - All circuit breakers are in closed position. - All controls in NORM, AUTO or OFF position. (a) Make sure that the aircraft is electrically grounded, refer to AMM Task 12-34-24-860-802. (b) In the cockpit, put warning notices in position to tell persons not to operate the flight controls. (c) Open, safety and tag the circuit breakers as given in the rudder inspection/check Job Set-up procedure, refer to AMM 55-40-00, Page Block 601. (d) Depressurize the Green Hydraulic System, refer to AMM Task 29-00-00-864-801. (e) Depressurize the Blue Hydraulic System, refer to AMM Task 29-00-00-864-802. (f) Depressurize the Yellow Hydraulic System, refer to AMM Task 29-00-00-864-803. (g) Put a warning notice in the cockpit to tell persons not to pressurize the hydraulic systems. (h) Put access platform(s) in position at the rudder.

DATE: Feb 07/13 SERVICE BULLETIN No.: A340-55-5007 REVISION No.: 01 - Aug 20/14 Page: 27 6

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# @A340-500/600 SERVICE BULLETIN C. PROCEDURE (1) Subtask 555007-832-201-001 - Check the rudder repair records Manpower Resources Manhours 4.00 Minimum number of person 1 Subtask elapsed time 4.00 Skills NON DESTRUCTIVE TESTING References Fig. A-GBAAA Rudder SN identification Sheet 01 Fig. A-GBCAA Repair type identification Sheet 01 - SRM list Fig. A-GBHAA Report sheet and sketches Sheet 01 - Pulse thermography report sheet Sheet 02 - Repair records report sheet Sheet 03 Sheet 04 Fig. A-GBJAA GFRP area location Sheet 01 Sheet 02 (a) Identify the Serial Number (SN) and the Part Number (PN) of the installed rudder. 1 Check the Aircraft Inspection Report and the maintenance records to verify the rudder identification and a potential rudder swap since EIS. 2 In case of doubts, check the rudder identification plate on the aircraft, as shown on Fig. A-GBAAA Sheet 01
. 3 If you do not find a SN/PN placard on the rudder, contact AIRBUS for further instructions. (b) Check the completeness of the rudder records and report the result to AIRBUS. Use the report sheet Fig. A-GBHAA Sheet 02
. NOTE : This action is not necessary, if the information has been already sent to AIRBUS in accordance with the OIT 999.0071/10 and the situation did not change since then. (c) Check the rudder records if repairs are recorded since rudder EIS. 1 Repairs not affected by this Service Bulletin are those which: - have been covered by AIRBUS Repair Design Approval Sheet (RDAS) after April 2010, - have been accomplished in accordance with the SRM A340 200/300 as listed in Fig. A-GBCAA Sheet 01 ,
DATE: Feb 07/13 SERVICE BULLETIN No.: A340-55-5007 REVISION No.: 01 - Aug 20/14 Page: 28 6

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# @A340-500/600 SERVICE BULLETIN - have been done in accordance with the SRM A340 200/300 revision April 2010 or later. 2 Report the result to AIRBUS. Use the report sheet Fig. A-GBHAA Sheet 02
. NOTE : This action is not necessary, if the information has been already sent to AIRBUS in accordance with the OIT 999.0071/10 and the situation did not change since then. 3 If repairs are recorded and the repair records are complete, refer to: - Subtask 555007-832-201-001 of this Service Bulletin for the rudder side shell areas made of CFRP. - Subtask 555007-832-207-001 of this Service Bulletin for the upper rudder side shell areas made of GFRP. NOTE : The outer skin ply of the upper area of the rudders is made of GFRP. GFRP areas require different pulse thermography inspection parameter than CFRP areas and additionally Tap test inspection or Woodpecker inspection have to be performed. For the identification of the GFRP areas, refer to Fig. A-GBJAA Sheet 02
. 4 If no repairs have been duly recorded, report the result to AIRBUS. Use the report sheet Fig. A-GBHAA Sheet 02
. No further action is necessary in accordance with this Service Bulletin. 5 In case of any doubts about the accomplishment of repairs, refer to: - Subtask 555007-832-203-001 of this Service Bulletin for the rudder side shell areas made of CFRP. - Subtask 555007-832-207-001 of this Service Bulletin for the upper rudder side shell areas made of GFRP. 6 If the repair records are not complete or not available, refer to: - Subtask 555007-832-203-001 of this Service Bulletin for the rudder side shell areas made of CFRP. - Subtask 555007-832-207-001 of this Service Bulletin for the upper rudder side shell areas made of GFRP. NOTE : The outer skin ply of the upper area of the rudders is made of GFRP. GFRP areas require different pulse thermography inspection parameter than CFRP areas and additionally Tap test inspection or Woodpecker inspection have to be performed. For the identification of the GFRP areas, refer to Fig. A-GBJAA Sheet 02
.

DATE: Feb 07/13 SERVICE BULLETIN No.: A340-55-5007 REVISION No.: 01 - Aug 20/14 Page: 29 6

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# @A340-500/600 SERVICE BULLETIN (2) Subtask 555007-832-202-001 - Identify the type, location and size of in-service repairs on the rudder side shell CFRP areas in case of complete repair records since rudder Entry Into Service (EIS) are available Manpower Resources Manhours 0 Minimum number of person 2 Subtask elapsed time 0 Skills NON DESTRUCTIVE TESTING Material necessary to do the job Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTESNon Aqueous CleanerGeneral 08BAA9 As required Textile-Lint Free Cotton 14SBA1 As required References Non Destructive Test Manual (NTM) Task 55-40-50-290-801 Structural Repair Manual (SRM) 51-75-11 51-75-12 Fig. A-GBBAA Repair type identification Sheet 01 Sheet 02 Fig. A-GBDAA Booster area definition Sheet 01 Sheet 02 Sheet 03 Fig. A-GBEAA Typical pulse thermography and ELCH/UT inspection Sheet 01 Sheet 02 - Repair size assessment Sheet 03 - Repair size assessment Sheet 04 - Boundary and grid of ELCH/UT inspections Sheet 05 - ELCH inspection grid Fig. A-GBHAA Report sheet and sketches Sheet 01 - Pulse thermography report sheet Sheet 02 - Repair records report sheet Sheet 03 Sheet 04 Fig. A-GFAAA Flow Chart Sheet 01 - Flow Chart 1 Sheet 02 - Flow Chart 2 Sheet 03 - Flow Chart 3 Sheet 04 - Flow Chart 4 Sheet 05 - Flow Chart 5 Sheet 06

DATE: Feb 07/13 SERVICE BULLETIN No.: A340-55-5007 REVISION No.: 01 - Aug 20/14 Page: 30 6

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# @A340-500/600 SERVICE BULLETIN
References Fig. A-GABAA Paint borer instructions Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 Sheet 08 (a) If no repair has been done or the recorded repair is not to be inspected in accordance with this Service Bulletin, report to AIRBUS. Use the report sheet Fig. A-GBHAA Sheet 02
. NOTE : This action is not necessary, if the information has been already sent to AIRBUS in accordance with the OIT 999.0071/10 and the situation did not change since then. No further action is necessary in accordance with this Service Bulletin. (b) If a repair must be inspected in accordance with this Service Bulletin, do the subsequent work steps in accordance with the Flow Chart Fig. A-GFAAA Sheet 01 : 1 Identify the repair type, refer to Fig. A-GBBAA Sheet 01 and Fig. A-GBBAA Sheet 02
. 2 Make sure that the paint thickness in the areas to be inspected by pulse thermography does not exceed: - 800 microns. - 400 microns below the decal foil if a decal foil is installed. NOTE : It is the responsibility of the operator to ensure that the paint thickness in all areas to be inspected is below or equal to the limits given above. a If the paint coating and/or logo application is too thick, abrade the paint in accordance with the SRM 51-75-11 to a thickness below or equal to the limits given above. NOTE : Chemical paint stripping is not allowed. b In case of doubts about the paint thickness, measure the thickness using a Paint Borer Kit, refer to the Figure Fig. A-GABAA Sheet 01 thru Fig. AGABAA Sheet 08
. <1> CAUTION : DO NOT DRILL DEEPLY INTO THE BASE MATERIAL (CFRP OR GFRP). DRILLING TOO DEEP LEADS TO DAMAGE IN THE OUTER SKIN
DATE: Feb 07/13 SERVICE BULLETIN No.: A340-55-5007 REVISION No.: 01 - Aug 20/14 Page: 31 6

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# @A340-500/600 SERVICE BULLETIN If you damage the outer skin with the paint borer, refer to the Subtask 555007-833-201-001 for repair instructions. 3 Clean the areas to be inspected with: Non Aqueous Cleaner-General 08BAA9 As required and Textile-Lint Free Cotton 14SBA1 As required

4 Do a pulse thermography inspection to get the precise location and the size of the repair, refer to NTM Task 55-40-50-290-801. NOTE : As an alternative for the pulse thermography inspection, you can identify the repair size by local sanding, refer to Subtask 555007-832-208-001. NOTE : The pulse thermography inspection indicates the outer skin repair ply geometry. The largest repair ply defines the boundary of the repair area. NOTE : In case of any findings (repair, damage, fluid ingress) during the pulse thermography inspection, save the images and send it together with the report sheet to AIRBUS. 5 Mark the boundary of the repair area, refer to Fig. A-GBEAA Sheet 02 and Fig. A-GBEAA Sheet 03
. 6 If fluid ingress has been detected during the pulse thermography inspection, refer to Subtask 555007-832-204-001 of this Service Bulletin. 7 Identify the booster areas in accordance with Fig. A-GBDAA Sheet 02 and Fig. A-GBDAA Sheet 03
. 8 If repairs in the booster areas up to 55000 mm 2 (85.25 sq.in.) have been detected, report the findings to AIRBUS. Use the report sheet Fig. A-GBHAA Sheet 01 and the rudder related sketches, refer to Fig. A-GBHAA Sheet 03 and Fig. A-GBHAA Sheet 04
. No further actions on these repairs in accordance with this Service Bulletin. 9 If repairs in the booster areas larger than 55000 mm 2 (85.25 sq.in.) have been detected, do the UT inspection around the repair in accordance with Subtask 555007-832-205-001 of this Service Bulletin. 10 If repairs not in the booster area have been detected, do the ELCH and/or UT inspection in accordance with Subtask 555007-832-205-001 of this Service Bulletin.

DATE: Feb 07/13 SERVICE BULLETIN No.: A340-55-5007 REVISION No.: 01 - Aug 20/14 Page: 32 6

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# @A340-500/600 SERVICE BULLETIN
11 After the inspection, restore the paint coating in accordance with the SRM 51-75-12. NOTE : Refer to OIT 999.0130/06 ’pai nt system - best practices’. (3) Subtask 555007-832-203-001 - Do a pulse thermography inspection on the complete rudder side shell CFRP areas to identify possible rudder in-service repairs in case of repair records are not complete or not available Manpower Resources Manhours 32.00 Minimum number of person 2 Subtask elapsed time 16 Skills NON DESTRUCTIVE TESTING Material necessary to do the job Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTESNon Aqueous CleanerGeneral 08BAA9 As required Textile-Lint Free Cotton 14SBA1 As required References Non Destructive Test Manual (NTM) Task 55-40-50-290-801 Structural Repair Manual (SRM) 51-75-11 51-75-12 Fig. A-GFAAA Flow Chart Sheet 01 - Flow Chart 1 Sheet 02 - Flow Chart 2 Sheet 03 - Flow Chart 3 Sheet 04 - Flow Chart 4 Sheet 05 - Flow Chart 5 Sheet 06 Fig. A-GBDAA Booster area definition Sheet 01 Sheet 02 Sheet 03 Fig. A-GBHAA Report sheet and sketches Sheet 01 - Pulse thermography report sheet Sheet 02 - Repair records report sheet Sheet 03 Sheet 04 Fig. A-GABAA Paint borer instructions Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 Sheet 08 DATE: Feb 07/13 SERVICE BULLETIN No.: A340-55-5007 REVISION No.: 01 - Aug 20/14 Page: 33 6

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# @A340-500/600 SERVICE BULLETIN (a) Do the subsequent work steps in accordance with the Flow Chart Fig. A-GFAAA Sheet 01 : 1 Report undocumented rudder S/N list to AIRBUS. a To get related rudder manufacturing rework data, provide AIRBUS with the rudder P/N, S/N and aircraft MSN in accordance with the accomplishment timescale instructions, refer to Para 1.E table 2A of this Service Bulletin. The manufacturing rework data will be provided through drawings covered by Mod. 202490. 2 Make sure that the paint thickness in the areas to be inspected by pulse thermography does not exceed: - 800 microns. - 400 microns below the decal foil if a decal foil is installed. NOTE : It is the responsibility of the operator to ensure that the paint thickness in all areas to be inspected is below or equal to the limits given above. a If the paint coating and/or logo application is too thick, abrade the paint in accordance with the SRM 51-75-11 to a thickness below or equal to the limits given above. NOTE : Chemical paint stripping is not allowed. b In case of doubts about the paint thickness, measure the thickness using a Paint Borer Kit, refer to the Figure Fig. A-GABAA Sheet 01 thru Fig. AGABAA Sheet 08
. <1> CAUTION : DO NOT DRILL DEEPLY INTO THE BASE MATERIAL (CFRP OR GFRP). DRILLING TOO DEEP LEADS TO DAMAGE IN THE OUTER SKIN If you damage the outer skin with the paint borer, refer to the Subtask 555007-833-201-001 for repair instructions. 3 Clean the areas to be inspected with: Non Aqueous Cleaner-General 08BAA9 As required and Textile-Lint Free Cotton 14SBA1 As required

DATE: Feb 07/13 SERVICE BULLETIN No.: A340-55-5007 REVISION No.: 01 - Aug 20/14 Page: 34 6

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# @A340-500/600 SERVICE BULLETIN
4 Do a pulse thermography inspection on the complete side shell CFRP areas (LH/RH) to identify repairs, refer to NTM Task 55-40-50-290-801. NOTE : The pulse thermography inspection indicates the outer skin repair ply geometry. The largest repair ply defines the boundary of the repair area. NOTE : In case of any findings (repair, damage, fluid ingress) during the pulse thermography inspection, save the images and send it together with the report sheet to AIRBUS. 5 If no repair has been detected during the pulse thermography inspection, report the result to AIRBUS. Use the report sheet Fig. A-GBHAA Sheet 01
. No further action is necessary in accordance with this Service Bulletin. 6 If fluid ingress has been detected during the thermograhy inspection, refer to Subtask 555007-832-204-001 of this Service Bulletin. 7 Identify the booster areas in accordance with Fig. A-GBDAA Sheet 02 and Fig. A-GBDAA Sheet 03
. 8 If repairs in the booster areas up to 55000 mm 2 (85.25 sq.in.) have been detected which are not manufacturing rework, report the findings to AIRBUS. Use the report sheet Fig. A-GBHAA Sheet 01 and the rudder related sketches, refer to Fig. A-GBHAA Sheet 03 and Fig. A-GBHAA Sheet 04
. No further actions on these repairs in accordance with this Service Bulletin. 9 If repairs in the booster areas larger than 55000 mm 2 (85.25 sq.in.) have been detected which are not manufacturing rework, do the UT inspection around the repairs in accordance with the Subtask 555007-832-205-001 of this Service Bulletin. 10 If repairs have been detected during the pulse thermography inspection which are not manufacturing rework and not in the booster areas, do the ELCH and/or UT inspection around the repairs in accordance with the Subtask 555007-832-205-001 of this Service Bulletin. 11 After the inspection, restore the paint coating in accordance with the SRM 51-75-12. NOTE : Refer to OIT 999.0130/06 ’pai nt system - best practices’. (4) Subtask 555007-832-204-001 - Do the corrective actions in case of fluid ingress detected Manpower Resources Manhours 0 Minimum number of person 1 Subtask elapsed time 0 Skills NON DESTRUCTIVE TESTING DATE: Feb 07/13 SERVICE BULLETIN No.: A340-55-5007 REVISION No.: 01 - Aug 20/14 Page: 35 6

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# @A340-500/600 SERVICE BULLETIN Material necessary to do the job Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTESAdhesive Film TapeAluminium Foil 05RAB9 As required Pressure Sensitive Tape 05RFB1 As required Self-Adhes. Disks 05TNB1 As required Methyl-Ethyl-Ketone 08BBF1 As required Trichloroethane Legacy 08BBU9 As required Laminating Resin-Epoxy Srm Type 2 - 13EBC1 As required References Non Destructive Test Manual (NTM) 51-10-25 Task 55-40-50-290-801 Fig. A-GFAAA Flow Chart Sheet 01 - Flow Chart 1 Sheet 02 - Flow Chart 2 Sheet 03 - Flow Chart 3 Sheet 04 - Flow Chart 4 Sheet 05 - Flow Chart 5 Sheet 06 Fig. A-GBHAA Report sheet and sketches Sheet 01 - Pulse thermography report sheet Sheet 02 - Repair records report sheet Sheet 03 Sheet 04 Fig. A-GBFAA Core ventilation procedure Sheet 01 Sheet 02 Sheet 03 Fig. A-GAAAA Closing of ventilation holes Sheet 01 Sheet 02 (a) If fluid ingress has been detected, continue with the subsequent work steps in accordance with the Flow Chart Fig. A-GFAAA Sheet 03 : 1 Around the identified fluid ingress, do the ELCH and/or UT inspection in accordance with the Subtask 555007-832-205-001 of this Service Bulletin. 2 If a damage has been detected during the ELCH and/or UT inspection, contact AIRBUS and follow their instructions. Use the report sheet Fig. A-GBHAA Sheet 01
. 3 If local single spots up to 1500 mm 2 (2.33 sq.in.) with fluid ingress have been detected, report the findings to AIRBUS. Use the report sheet Fig. A-GBHAA Sheet 01 and the rudder related sketches, refer to Fig. A-GBHAA Sheet 03 and Fig. A-GBHAA Sheet 04
. No further actions on these local single spots of fluid ingress in accordance with this Service Bulletin. DATE: Feb 07/13 SERVICE BULLETIN No.: A340-55-5007 REVISION No.: 01 - Aug 20/14 Page: 36 6

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# @A340-500/600 SERVICE BULLETIN
4 If a maximum of 5 local single spots per side shell larger than 1500 mm 2 (2.33 sq.in.) and up to 5000 mm 2 (7.75 sq.in.) have been detected, do the ventilation of the rudder core: a CAUTION : TO DRILL THE HOLES APPLY MODERATE PRESSURE TO PREVENT DAMAGE TO THE SKIN, AT THE END OF THE DRILLING OPERATION. DO NOT DRILL THE OPPOSITE SHELL. Drill the holes to a DIA of 3.0 mm (0.12 in.) through the outer and inner skin in accordance with the dimensions shown on Fig. A-GBFAA Sheet 02 and Fig. A-GBFAA Sheet 03
. NOTE : Spots of fluid ingress behind the trailing edge screw line must not be vented. b Temporary restoration of the drain holes option 1: <1> Close the drain holes with: Adhesive Film Tape- Aluminium Foil 05RAB9 As required

or Self-Adhes. Disks 05TNB1 As required <2> Do repetitive detailed inspections of the restored area for loose or lost adhesive disks or tape until the repair of the affected area has been done. <3> In case of loose or lost tape or disks, close the holes again with: Adhesive Film Tape- Aluminium Foil 05RAB9 As required

or Self-Adhes. Disks 05TNB1 As required c Temporary restoration of the drain holes option 2: <1> Close the drain holes in accordance with the instructions given in the Figure Fig. A-GAAAA Sheet 01 and Fig. A-GAAAA Sheet 02
. <a> Consumable Material necessary to close the drain holes: Pressure Sensitive Tape 05RFB1 As required

DATE: Feb 07/13 SERVICE BULLETIN No.: A340-55-5007 REVISION No.: 01 - Aug 20/14 Page: 37 6

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# @A340-500/600 SERVICE BULLETINLaminating ResinEpoxy Srm Type 2 - 13EBC1 As required Methyl-Ethyl-Ketone 08BBF1 As required Trichloroethane Legacy 08BBU9 As required 5 Do repetitive thermography inspections until the repair of the affected area has been done, refer to NTM 51-10-25 (preferred) or refer to NTM Task 55-40-50-290-801. NOTE : In case of any findings during the pulse thermography inspection, save the images and send it together with the report sheet to AIRBUS. 6 Do the repair in accordance with the SRM. Due to the pending availability of the SRM improved repair, contact AIRBUS for detailed repair instructions. 7 Report the repair to AIRBUS. Use the report sheet Fig. A-GBHAA Sheet 02
. 8 If more than 5 local single spots per side shell larger than 1500 mm 2 (2.33 sq.in.) and up to 5000 mm 2 (7.75 sq.in.) have been detected, report to AIRBUS and follow their instructions. Use the report sheet Fig. A-GBHAA Sheet 01
. 9 If local single spots larger than 5000 mm 2 (7.75 sq.in.) with fluid ingress have been detected, report the findings to AIRBUS and follow their instructions. Use the report sheet Fig. A-GBHAA Sheet 01
. (5) Subtask 555007-832-205-001 - Do the ELCH and/or UT inspection around identified repairs/fluid ingress Manpower Resources Manhours 0 Minimum number of person 1 Subtask elapsed time 0 Skills NON DESTRUCTIVE TESTING Material necessary to do the job Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTESNon Aqueous CleanerGeneral 08BAA9 As required Textile-Lint Free Cotton 14SBA1 As required
DATE: Feb 07/13 SERVICE BULLETIN No.: A340-55-5007 REVISION No.: 01 - Aug 20/14 Page: 38 6

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# @A340-500/600 SERVICE BULLETIN
References Non Destructive Test Manual (NTM) 51-10-24 51-10-26 55-40-09 Para 2.C Fig. A-GBEAA Typical pulse thermography and ELCH/UT inspection Sheet 01 Sheet 02 - Repair size assessment Sheet 03 - Repair size assessment Sheet 04 - Boundary and grid of ELCH/UT inspections Sheet 05 - ELCH inspection grid Fig. A-GBGAA Rudder skin thickness identification Sheet 01 Sheet 02 Sheet 03 Fig. A-GBHAA Report sheet and sketches Sheet 01 - Pulse thermography report sheet Sheet 02 - Repair records report sheet Sheet 03 Sheet 04 (a) If necessary, clean the areas to be inspected with: Non Aqueous Cleaner-General 08BAA9 As required

and Textile-Lint Free Cotton 14SBA1 As required (b) Identify the skin thickness of the areas to be inspected, refer to Fig. A-GBGAA Sheet 02 and Fig. A-GBGAA Sheet 03
. (c) If the skin thickness of the affected areas does not exceed 1.5 mm (0.06 in.), do an ELCH inspection around the marked repair areas, refer to NTM 51-10-26. 1 For the ELCH inspection, use a grid of 75 mm x 75 mm from the boundary of the largest repair ply up to 200 mm around the largest repair ply, refer to Fig. A-GBEAA Sheet 04
. a For the adjustment of the ELCH, refer to NTM 51-10-26. b For the assessment criteria (yellow and red values) for the ELCH inspection, refer to NTM 55-40-09 Para 2.C. (d) If the skin of the affected areas is thicker than 1.5 mm (0.06 in.), do an UT inspection around the marked repair areas, refer to NTM 51-10-24. 1 Do the UT inspection in an area between the boundary of the largest repair ply up to 75 mm around the largest repair ply, refer to Fig. A-GBEAA Sheet 04
.

DATE: Feb 07/13 SERVICE BULLETIN No.: A340-55-5007 REVISION No.: 01 - Aug 20/14 Page: 39 6

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# @A340-500/600 SERVICE BULLETIN (e) If a damage has been detected during the ELCH/UT inspection, provide detailed information of the identified repair, report to AIRBUS and follow their instructions. Use the report sheet Fig. A-GBHAA Sheet 02 and the rudder related sketches, refer to Fig. A-GBHAA Sheet 03 and Fig. A-GBHAA Sheet 04
. (f) If no damage has been detected during the ELCH/UT inspection, continue with the steps given in the Subtask 555007-832-206-001 of this Service Bulletin. (6) Subtask 555007-832-206-001 - Do terminating actions in case of no damage detected Manpower Resources Manhours 0 Minimum number of person 1 Subtask elapsed time 0 Skills NON DESTRUCTIVE TESTING Material necessary to do the job Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTESAdhesive Film TapeAluminium Foil 05RAB9 As required Pressure Sensitive Tape 05RFB1 As required Self-Adhes. Disks 05TNB1 As required Methyl-Ethyl-Ketone 08BBF1 As required Trichloroethane Legacy 08BBU9 As required Laminating Resin-Epoxy Srm Type 2 - 13EBC1 As required References Fig. A-GBFAA Core ventilation procedure Sheet 01 Sheet 02 Sheet 03 Fig. A-GBHAA Report sheet and sketches Sheet 01 - Pulse thermography report sheet Sheet 02 - Repair records report sheet Sheet 03 Sheet 04 Fig. A-GFAAA Flow Chart Sheet 01 - Flow Chart 1 Sheet 02 - Flow Chart 2 Sheet 03 - Flow Chart 3 Sheet 04 - Flow Chart 4 Sheet 05 - Flow Chart 5 Sheet 06 Fig. A-GAAAA Closing of ventilation holes Sheet 01 Sheet 02
DATE: Feb 07/13 SERVICE BULLETIN No.: A340-55-5007 REVISION No.: 01 - Aug 20/14 Page: 40 6

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# @A340-500/600 SERVICE BULLETIN (a) If no damage has been detected, continue with the subsequent work steps in accordance with the Flow Chart Fig. A-GFAAA Sheet 02 : 1 If a repair up to 10000 mm 2 (15.50 sq.in.) has been detected, provide detailed information about the repair and report to AIRBUS. Use the report sheet Fig. A-GBHAA Sheet 02 and the rudder related sketches, refer to Fig. A-GBHAA Sheet 03 and Fig. A-GBHAA Sheet 04
. 2 If a repair larger than 10000 mm 2 (15.50 sq.in.) and up to 20000 mm 2 (31.00 sq.in.) has been detected, do the ventilation of the core: NOTE : Instead of the core ventilation procedure, you can do repetitive ELCH and/or UT inspections around the repair areas until the repair has been done, refer to Subtask 555007-832-205-001. a CAUTION : TO DRILL THE HOLES APPLY MODERATE PRESSURE TO PREVENT DAMAGE TO THE SKIN, AT THE END OF THE DRILLING OPERATION. DO NOT DRILL THE OPPOSITE SHELL. Drill the holes to a DIA of 3.0 mm (0.12 in.) through the outer and inner skin in accordance with the dimensions shown on Fig. A-GBFAA Sheet 02 and Fig. A-GBFAA Sheet 03
. NOTE : Repairs behind the trailing edge screw line must not be vented. b Temporary restoration of the drain holes option 1: <1> Close the drain holes with: Adhesive Film Tape- Aluminium Foil 05RAB9 As required

or Self-Adhes. Disks 05TNB1 As required <2> Do repetitive detailed inspections of the restored area for loose or lost adhesive disks or tape until the repair of the affected area has been done. <3> In case of loose or lost tape or disks, close the holes again with: Adhesive Film Tape- Aluminium Foil 05RAB9 As required

or Self-Adhes. Disks 05TNB1 As required DATE: Feb 07/13 SERVICE BULLETIN No.: A340-55-5007 REVISION No.: 01 - Aug 20/14 Page: 41 6

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# @A340-500/600 SERVICE BULLETIN

c Temporary restoration of the drain holes option 2: <1> Close the drain holes in accordance with the instructions given in the Figure Fig. A-GAAAA Sheet 01 and Fig. A-GAAAA Sheet 02
. <a> Consumable Material necessary to close the drain holes: Pressure Sensitive Tape 05RFB1 As requiredLaminating ResinEpoxy Srm Type 2 - 13EBC1 As required Methyl-Ethyl-Ketone 08BBF1 As required Trichloroethane Legacy 08BBU9 As required d Report the results and the planned terminating action to AIRBUS. Use the report sheet Fig. A-GBHAA Sheet 02
. e Do the terminating action in accordance with the SRM. Due to the pending availability of the SRM improved repair, contact AIRBUS for detailed repair instructions. NOTE : The new repair cutout is equal to the largest outer skin repair ply. 3 If a repair larger than 20000 mm 2 (31.00 sq.in.) and up to 80000 mm 2 (124 sq.in.) has been detected, do the ventilation of the core: a CAUTION : TO DRILL THE HOLES APPLY MODERATE PRESSURE TO PREVENT DAMAGE TO THE SKIN, AT THE END OF THE DRILLING OPERATION. DO NOT DRILL THE OPPOSITE SHELL. Drill the holes to a DIA of 3.0 mm (0.12 in.) through the outer and inner skin in accordance with the dimensions shown on Fig. A-GBFAA Sheet 02 and Fig. A-GBFAA Sheet 03
. b Temporary restoration of the drain holes option 1: <1> Close the drain holes with: Adhesive Film Tape- Aluminium Foil 05RAB9 As required

or
DATE: Feb 07/13 SERVICE BULLETIN No.: A340-55-5007 REVISION No.: 01 - Aug 20/14 Page: 42 6

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# @A340-500/600 SERVICE BULLETIN
Self-Adhes. Disks 05TNB1 As required <2> Do repetitive detailed inspections of the restored area for loose or lost adhesive disks or tape until the repair of the affected area has been done. <3> In case of loose or lost tape or disks, close the holes again with: Adhesive Film Tape- Aluminium Foil 05RAB9 As required

or Self-Adhes. Disks 05TNB1 As required c Temporary restoration of the drain holes option 2: <1> Close the drain holes in accordance with the instructions given in the Figure Fig. A-GAAAA Sheet 01 and Fig. A-GAAAA Sheet 02
. <a> Consumable Material necessary to close the drain holes: Pressure Sensitive Tape 05RFB1 As requiredLaminating ResinEpoxy Srm Type 2 - 13EBC1 As required Methyl-Ethyl-Ketone 08BBF1 As required Trichloroethane Legacy 08BBU9 As required d Report the results and the planned terminating action to AIRBUS. Use the report sheet Fig. A-GBHAA Sheet 02
. e Do the terminating action in accordance with the SRM. NOTE : The new repair cutout is equal to the largest outer skin repair ply. NOTE : If the repair is larger than 30000 mm 2 (46.50 sq.in.), contact AIRBUS for additional instructions. 4 If a repair larger than 80000 mm 2 (124 sq.in.) has been detected, do the ventilation of the core: a

DATE: Feb 07/13 SERVICE BULLETIN No.: A340-55-5007 REVISION No.: 01 - Aug 20/14 Page: 43 6

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# @A340-500/600 SERVICE BULLETIN CAUTION : TO DRILL THE HOLES APPLY MODERATE PRESSURE TO PREVENT DAMAGE TO THE SKIN, AT THE END OF THE DRILLING OPERATION. DO NOT DRILL THE OPPOSITE SHELL. Drill the holes to a DIA of 3.0 mm (0.12 in.) through the outer and inner skin in accordance with the dimensions shown on Fig. A-GBFAA Sheet 02 and Fig. A-GBFAA Sheet 03
. b Temporary restoration of the drain holes option 1: <1> Close the drain holes with: Adhesive Film Tape- Aluminium Foil 05RAB9 As required

or Self-Adhes. Disks 05TNB1 As required <2> Do repetitive detailed inspections of the restored area for loose or lost adhesive disks or tape until the repair of the affected area has been done. <3> In case of loose or lost tape or disks, close the holes again with: Adhesive Film Tape- Aluminium Foil 05RAB9 As required

or Self-Adhes. Disks 05TNB1 As required c Temporary restoration of the drain holes option 2: <1> Close the drain holes in accordance with the instructions given in the Figure Fig. A-GAAAA Sheet 01 and Fig. A-GAAAA Sheet 02
. <a> Consumable Material necessary to close the drain holes: Pressure Sensitive Tape 05RFB1 As requiredLaminating ResinEpoxy Srm Type 2 - 13EBC1 As required Methyl-Ethyl-Ketone 08BBF1 As required Trichloroethane Legacy 08BBU9 As required

DATE: Feb 07/13 SERVICE BULLETIN No.: A340-55-5007 REVISION No.: 01 - Aug 20/14 Page: 44 6

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# @A340-500/600 SERVICE BULLETIN d Report the results and the planned terminating action to AIRBUS. Use the report sheet Fig. A-GBHAA Sheet 02
. e Do the terminating action: Replace the rudder in accordance with the grace period given in the accomplishment timescale table or replace the affected rudder shell. NOTE : The rudder shell replacement can be done only at the AIRBUS Stade facility. Before sending the rudder, contact: AIRBUS Department SBO5 Monitored Retrofit Campaign Account MONITORED.RETROFIT@airbus.com to validate the feasibility of the rudder shell replacement. No further action is necessary in accordance with this Service Bulletin. (7) Subtask 555007-832-207-001 - Inspect the rudder side shell upper GFRP areas Manpower Resources Manhours 0 Minimum number of person 1 Subtask elapsed time 0 Skills NON DESTRUCTIVE TESTING Material necessary to do the job Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTESNon Aqueous CleanerGeneral 08BAA9 As required Textile-Lint Free Cotton 14SBA1 As required References Non Destructive Test Manual (NTM) Task 51-10-03-280-801 Task 51-10-19-280-801 Task 55-40-50-290-801 Structural Repair Manual (SRM) 51-75-11 51-75-12 Fig. A-GBBAA Repair type identification Sheet 01 Sheet 02

DATE: Feb 07/13 SERVICE BULLETIN No.: A340-55-5007 REVISION No.: 01 - Aug 20/14 Page: 45 6

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# @A340-500/600 SERVICE BULLETIN
References Fig. A-GFAAA Flow Chart Sheet 01 - Flow Chart 1 Sheet 02 - Flow Chart 2 Sheet 03 - Flow Chart 3 Sheet 04 - Flow Chart 4 Sheet 05 - Flow Chart 5 Sheet 06 Fig. A-GBEAA Typical pulse thermography and ELCH/UT inspection Sheet 01 Sheet 02 - Repair size assessment Sheet 03 - Repair size assessment Sheet 04 - Boundary and grid of ELCH/UT inspections Sheet 05 - ELCH inspection grid Fig. A-GABAA Paint borer instructions Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 Sheet 08 (a) If repairs in the rudder side shell upper GFRP area are recorded, do the subsequent inspections in accordance with the Flow Chart Fig. A-GFAAA Sheet 04 : 1 Make sure that the paint thickness in the areas to be inspected by pulse thermography does not exceed: - 400 microns. - 400 microns below the decal foil if a decal foil is installed. NOTE : It is the responsibility of the operator to ensure that the paint thickness in all areas to be inspected is below or equal to the limit of 400 microns. a If the paint coating and/or logo application is too thick, abrade the paint in accordance with the SRM 51-75-11 to a thickness below or equal to the limit of 400 microns. NOTE : Chemical paint stripping is not allowed. b In case of doubts about the paint thickness, measure the thickness using a Paint Borer Kit, refer to the Figure Fig. A-GABAA Sheet 01 thru Fig. AGABAA Sheet 08
. <1> CAUTION : DO NOT DRILL DEEPLY INTO THE BASE MATERIAL (CFRP OR GFRP). DRILLING TOO DEEP LEADS TO DAMAGE IN THE OUTER SKIN
DATE: Feb 07/13 SERVICE BULLETIN No.: A340-55-5007 REVISION No.: 01 - Aug 20/14 Page: 46 6

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# @A340-500/600 SERVICE BULLETIN If you damage the outer skin with the paint borer, refer to the Subtask 555007-833-201-001 for repair instructions. 2 Clean the areas to be inspected with: Non Aqueous Cleaner-General 08BAA9 As required and Textile-Lint Free Cotton 14SBA1 As required

3 Do a pulse thermography inspection to get the precise location and size of the repair, refer to NTM Task 55-40-50-290-801. NOTE : As an alternative for the pulse thermography inspection, you can identify the repair size by local sanding, refer to Subtask 555007-832-208-001. NOTE : The pulse thermography inspection indicates the outer skin repair ply geometry. The largest repair ply defines the boundary of the repair area. NOTE : Make sure that you use the pulse thermography inspection parameters for GFRP, refer to NTM Task 55-40-50-290-801. 4 Mark the boundary of the repair area, refer to Fig. A-GBEAA Sheet 02 and Fig. A-GBEAA Sheet 03
. 5 If a repair type A-A, refer to Fig. A-GBBAA Sheet 02 , has been identified, do a Tap test inspection on the repair, refer to NTM Task 51-10-03-280-801 or NTM Task 51-10-19-280-801, to identify a skin to core disbonding. 6 For all other repair types, do the ELCH and/or UT inspection around the repair, refer to the Subtask 555007-832-205-001 of this Service Bulletin. 7 If fluid ingress has been detected, refer to Subtask 555007-832-204-001 of this Service Bulletin. 8 For further actions continue with the instructions given in the Subtask 555007-832-206-001 and the actions in the Flow Chart Fig. A-GFAAA Sheet 02 of this Service Bulletin. 9 After the inspection, restore the paint coating in accordance with the SRM 51-75-12. NOTE : Refer to OIT 999.0130/06 ’pai nt system - best practices’.

DATE: Feb 07/13 SERVICE BULLETIN No.: A340-55-5007 REVISION No.: 01 - Aug 20/14 Page: 47 6

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

# @A340-500/600 SERVICE BULLETIN (b) If there is no information about repairs in the rudder side shell upper GFRP area, do the subsequent inspections in accordance with the Flow Chart Fig. A-GFAAA Sheet 04 : 1 Make sure that the paint thickness in the areas to be inspected by pulse thermography does not exceed: - 400 microns. - 400 microns below the decal foil if a decal foil is installed. NOTE : It is the responsibility of the operator to ensure that the paint thickness in all areas to be inspected is below or equal to the limit of 400 microns. a If the paint coating and/or logo application is too thick, abrade the paint in accordance with the SRM 51-75-11 to a thickness below or equal to the limit of 400 microns. NOTE : Chemical paint stripping is not allowed. b In case of doubts about the paint thickness, measure the thickness using a Paint Borer Kit, refer to the Figure Fig. A-GABAA Sheet 01 thru Fig. AGABAA Sheet 08
. <1> CAUTION : DO NOT DRILL DEEPLY INTO THE BASE MATERIAL (CFRP OR GFRP). DRILLING TOO DEEP LEADS TO DAMAGE IN THE OUTER SKIN If you damage the outer skin with the paint borer, refer to the Subtask 555007-833-201-001 for repair instructions. 2 Clean the areas to be inspected with: Non Aqueous Cleaner-General 08BAA9 As required and Textile-Lint Free Cotton 14SBA1 As required

3 Do a pulse thermography inspection on the complete GFRP area to identify repairs, refer to NTM Task 55-40-50-290-801. NOTE : The pulse thermography inspection indicates the outer skin repair ply geometry. The largest repair ply defines the boundary of the repair area. NOTE : Make sure that you use the pulse thermography inspection parameters for GFRP, refer to NTM Task 55-40-50-290-801.
DATE: Feb 07/13 SERVICE BULLETIN No.: A340-55-5007 REVISION No.: 01 - Aug 20/14 Page: 48 6

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# @A340-500/600 SERVICE BULLETIN
4 If repairs which are not manufacturing rework have been identified, mark the boundary of the repair area, refer to Fig. A-GBEAA Sheet 02 and Fig. AGBEAA Sheet 03
. 5 Do a Tap test inspection, refer to NTM Task 51-10-03-280-801 or NTM Task 51-10-19-280-801, on the complete GFRP area to identify a skin to core disbonding. 6 Do the ELCH and/or UT inspection around the repair, refer to the Subtask 555007-832-205-001 of this Service Bulletin. 7 If fluid ingress has been detected, refer to Subtask 555007-832-204-001 of this Service Bulletin. 8 For further actions continue with the instructions given in the Subtask 555007-832-206-001 and the actions in Flow Chart Fig. A-GFAAA Sheet 02 of this Service Bulletin. 9 After the inspection, restore the paint coating in accordance with the SRM 51-75-12. NOTE : Refer to OIT 999.0130/06 ’pai nt system - best practices’. (8) Subtask 555007-833-201-001 - Close the holes in case of drilling thru the outer skin during paint thickness measurement Manpower Resources Manhours 0 Minimum number of person 1 Subtask elapsed time 0 Skills NON SPECIFIC Material necessary to do the job Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTESAdhesive Film TapeAluminium Foil 05RAB9 As required Self-Adhes. Disks 05TNB1 As requiredNon Aqueous CleanerGeneral 08BAA9 As required Laminating Resin-Epoxy Srm Type 2 - 13EBC1 As required Textile-Lint Free Cotton 14SBA1 As required

DATE: Feb 07/13 SERVICE BULLETIN No.: A340-55-5007 REVISION No.: 01 - Aug 20/14 Page: 49 6

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# @A340-500/600 SERVICE BULLETIN
References Structural Repair Manual (SRM) 51-75-12 51-77-10 Para 5 51-77-11 Para 4.M.(2) 51-77-11 Para 4.A.(3) 51-77-11 Para 4.E 51-77-11 Para 5.D 51-77-11 Figure 14 (a) Hole closing procedure option 1: 1 WARNING : OBEY THE MANUFACTURER’S INSTRUCTIONS WHEN YOU USE CLEANING AGENTS, ADHESIVES, SEALANTS AND PAINTS: THESE MATERIALS ARE DANGEROUS. WARNING : WEAR THE CORRECT PROTECTIVE GLOVES, GOGGLES AND FILTER MASKS WHEN YOU USE CLEANING AGENTS, ADHESIVES, SEALANTS AND PAINTS: THESE MATERIALS ARE DANGEROUS. Prepare and dry the restoration area in accordance with the SRM 51-77-11 Para 4.M.(2). 2 Prepare in accordance with the SRM 51-77-11 Para 4.A.(3):Laminating ResinEpoxy Srm Type 2 - 13EBC1 As required NOTE : The data sheets for each adhesive, resin or low density compound states the maximum quantity that can be safely mixed at one time without causing an exotherm reaction. Always refer to the appropriate data sheet before mixing the chosen material. 3 Warm up the mixed resin to a maximum temperature of 45 ̊C (113 F). 4 Put the resin in a syringe volume 10 ml with a needle DIA 1.0 mm (0.04 in.) and inject the resin through the hole into the cells of the honeycomb core. Start the injection at the cell bottom and finish when the resin is leaking out of the hole. 5 Close the filled holes with Adhesive Film Tape- Aluminium Foil 05RAB9 As required

or Self-Adhes. Disks 05TNB1 As required
DATE: Feb 07/13 SERVICE BULLETIN No.: A340-55-5007 REVISION No.: 01 - Aug 20/14 Page: 50 6

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# @A340-500/600 SERVICE BULLETIN 6 Let the resin cure for a minimum of 6 hours at room temperature. If the room temperature is below 18 ̊C (64F), extend the curing time and perform a gelation test outside the restoration area. After resin gelation plus 2 h, the aircraft can be released to operations again. OR Cure the resin at 60 ̊C (140F) for 45 minutes. Install a heating blanket with a vacuum bag on the rudder surface in accordance with the SRM 51-77-11 Para 5.D, and control the temperature by means of thermocouples in accordance with the SRM 51-77-11 Figure 14. 7 Do the final surface restoration in accordance with the compliance time given in Para 1.E.(2), table 5: a Remove the self adhesive tape from the restoration areas. b Inspect the restoration in accordance with the SRM 51-77-10 Para 5. c Remove any surplus resin from the border area of the restoration. Use abrasive cloth. Start with 280 grade and finish with 400 grade. d Clean the restoration areas in accordance with the SRM 51-77-11 Para 4.E. Use: Non Aqueous Cleaner-General 08BAA9 As required and Textile-Lint Free Cotton 14SBA1 As required
e Restore the surface protection in accordance with the SRM 51-75-12. (b) Hole closing procedure option 2: 1 WARNING : OBEY THE MANUFACTURER’S INSTRUCTIONS WHEN YOU USE CLEANING AGENTS, ADHESIVES, SEALANTS AND PAINTS: THESE MATERIALS ARE DANGEROUS. WARNING : WEAR THE CORRECT PROTECTIVE GLOVES, GOGGLES AND FILTER MASKS WHEN YOU USE CLEANING AGENTS, ADHESIVES, SEALANTS AND PAINTS: THESE MATERIALS ARE DANGEROUS. Prepare and dry the restoration area in accordance with the SRM 51-77-11 Para 4.M.(2).

DATE: Feb 07/13 SERVICE BULLETIN No.: A340-55-5007 REVISION No.: 01 - Aug 20/14 Page: 51 6

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# @A340-500/600 SERVICE BULLETIN
2 Prepare in accordance with the SRM 51-77-11 Para 4.A.(3):Laminating ResinEpoxy Srm Type 2 - 13EBC1 As required NOTE : The data sheets for each adhesive, resin or low density compound states the maximum quantity that can be safely mixed at one time without causing an exotherm reaction. Always refer to the appropriate data sheet before mixing the chosen material. 3 Warm up the mixed resin to a maximum temperature of 45 ̊C (113 F). 4 Put the resin in a syringe volume 10 ml with a needle DIA 1.0 mm (0.04 in.) and inject the resin through the hole into the cells of the honeycomb core. Start the injection at the cell bottom and finish when the resin is leaking out of the hole. 5 Close the filled holes with Adhesive Film Tape- Aluminium Foil 05RAB9 As required

or Self-Adhes. Disks 05TNB1 As required

6 Let the resin cure for a minimum of 12 hours at room temperature. If the room temperature is below 18 ̊C (64F), extend the curing time and perform a gelation test outside the restoration area. After resin gelation plus 4 h, continue with the subsequent steps: a Remove the self adhesive tape from the restoration areas. b Inspect the restoration in accordance with the SRM 51-77-10 Para 5. c Remove any surplus resin from the border area of the restoration. Use abrasive cloth. Start with 280 grade and finish with 400 grade. d Clean the restoration areas in accordance with the SRM 51-77-11 Para 4.E. Use: Non Aqueous Cleaner-General 08BAA9 As required and Textile-Lint Free Cotton 14SBA1 As required
e Restore the surface protection in accordance with the SRM 51-75-12. DATE: Feb 07/13 SERVICE BULLETIN No.: A340-55-5007 REVISION No.: 01 - Aug 20/14 Page: 52 6

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# @A340-500/600 SERVICE BULLETIN (9) Subtask 555007-832-208-001 - Identify the repair size by local sanding Manpower Resources Manhours 0 Minimum number of person 1 Subtask elapsed time 0 Skills AIRFRAME References Non Destructive Test Manual (NTM) 55-40-50 Structural Repair Manual (SRM) 51-23-11 51-75-11 Para 3.D 51-75-12 51-77-10 51-77-11 Para 4.D 51-77-11 Para 4.E 51-77-11 Para 4.G Fig. A-GFAAA Flow Chart Sheet 01 - Flow Chart 1 Sheet 02 - Flow Chart 2 Sheet 03 - Flow Chart 3 Sheet 04 - Flow Chart 4 Sheet 05 - Flow Chart 5 Sheet 06 Fig. A-GBDAA Booster area definition Sheet 01 Sheet 02 Sheet 03 Fig. A-GBHAA Report sheet and sketches Sheet 01
- Pulse thermography report sheet Sheet 02
- Repair records report sheet Sheet 03 Sheet 04 Fig. A-GBEAA Typical pulse thermography and ELCH/UT inspection Sheet 01 Sheet 02 - Repair size assessment Sheet 03 - Repair size assessment Sheet 04 - Boundary and grid of ELCH/UT inspections Sheet 05 - ELCH inspection grid CAUTION : IT IS THE OPERATOR’S RESPONSIBILITY TO ENSURE THAT STRUCTURAL SIDE SHELL OUTER SKIN PLY (CFRP OR GFRP) IN ACCORDANCE WITH THE DESIGN DRAWING IS NOT DAMAGED DURING THE LOCAL SANDING PROCESS. REMARK: IN MOST OF THE RUDDER SURFACE THE OUTER SKIN CONSISTS ONLY OF ONE CFRP OR GFRP PLY. IN CASE OF SANDING DAMAGE IMMEDIATE REPAIR BEFORE NEXT FLIGHT IS REQUIRED. AN AREA DAMAGED BY THE LOCAL SANDING COMBINED WITH AN EXISTING REPAIR CAN LEAD TO A NON-REPAIRABLE SIZE AND SUBSEQUENT SIDE SHELL REPLACEMENT. NOTE : The local sanding procedure is only valid for fully documented repairs. DATE: Feb 07/13 SERVICE BULLETIN No.: A340-55-5007 REVISION No.: 01 - Aug 20/14 Page: 53 6

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# @A340-500/600 SERVICE BULLETIN (a) Do the subsequent work steps in accordance with the Flow Chart Fig. A-GFAAA Sheet 01 , beginning with the box ’LOCAL PAINT THICKNESS IDENTIFICATION’. 1 Identify the paint thickness and the initial basic primer on top of the repair and beside the repair location. NOTE : It is recommended to use a Paint Borer Kit Model 518, 518S or 518MC. 2 Clean the previous repair area in accordance with the SRM 51-77-11 Para 4.E. 3 Do a local mechanical sanding on top and around the repair in accordance with the SRM 51-75-11 Para 3.D on a step-by-step basis up to the initial basic primer layer. NOTE : The allowed maximum repair size is 1m 2 (10.76sq.ft.) per local repair. 4 If the largest repair ply is visible: a Remove the dust and dry the area in accordance with the SRM 51-77-11 Para 4.G. b Use a magnifying lens to inspect the sanded area for damage. <1> In case of findings, do the damage assessment in accordance with the SRM 51-77-10. c Mark the boundary of the repair area, refer to Fig. A-GBEAA Sheet 02 and Fig. A-GBEAA Sheet 03
. d Identify the booster areas in accordance with Fig. A-GBDAA Sheet 02 and Fig. A-GBDAA Sheet 03
. e If repairs in the booster areas up to 55000 mm 2 (85.25 sq.in.) have been detected, report the findings to AIRBUS. Use the report sheet Fig. A-GBHAA Sheet 02 and the rudder related sketches, refer to Fig. AGBHAA Sheet 03 and Fig. A-GBHAA Sheet 04
. <1> Restore the surface protection in accordance with the SRM 51-23-11. No further actions on these repairs in accordance with this Service Bulletin. f If repairs in the booster areas larger than 55000 mm 2 (85.25 sq.in.) have been detected, do the UT inspection around the repair in accordance with Subtask 555007-832-205-001 of this Service Bulletin. g If repairs not in the booster area have been detected, do the ELCH and/or UT inspection in accordance with Subtask 555007-832-205-001 of this Service Bulletin. DATE: Feb 07/13 SERVICE BULLETIN No.: A340-55-5007 REVISION No.: 01 - Aug 20/14 Page: 54 6

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# @A340-500/600 SERVICE BULLETIN h If fluid ingress has been detected during the pulse thermography inspection, refer to Subtask 555007-832-204-001 of this Service Bulletin. i After the inspection, restore the paint coating in accordance with the SRM 51-75-12 and SRM 51-23-11. NOTE : Refer to OIT 999.0130/06 ’pai nt system - best practices’. 5 If the largest repair ply is not visible, continue the local mechanical sanding on top and around the repair in accordance with the SRM 51-77-11 Para 4.D on a step-by-step basis up to the pore filler or adhesive with a radius of approximately 50.0mm (1.97in.) beyond the initial detected repair patch. 6 If the largest repair ply is visible now: a Remove the dust and dry the area in accordance with the SRM 51-77-11 Para 4.G. b Mark the boundary of the repair area, refer to Fig. A-GBEAA Sheet 02 and Fig. A-GBEAA Sheet 03
. c Use a magnifying lens to inspect the sanded area for damage. d In case of findings, do the damage assessment in accordance with the SRM 51-77-10. e Identify the booster areas in accordance with Fig. A-GBDAA Sheet 02 and Fig. A-GBDAA Sheet 03
. f If repairs in the booster areas up to 55000 mm 2 (85.25 sq.in.) have been detected, report the findings to AIRBUS. Use the report sheet Fig. A-GBHAA Sheet 02 and the rudder related sketches, refer to Fig. AGBHAA Sheet 03 and Fig. A-GBHAA Sheet 04
. <1> Restore the surface protection in accordance with the SRM 51-23-11. No further actions on these repairs in accordance with this Service Bulletin. g If repairs in the booster areas larger than 55000 mm 2 (85.25 sq.in.) have been detected, do the UT inspection around the repair in accordance with Subtask 555007-832-205-001 of this Service Bulletin. h If repairs not in the booster area have been detected, do the ELCH and/or UT inspection in accordance with Subtask 555007-832-205-001 of this Service Bulletin. i If fluid ingress has been detected during the pulse thermography inspection, refer to Subtask 555007-832-204-001 of this Service Bulletin.

DATE: Feb 07/13 SERVICE BULLETIN No.: A340-55-5007 REVISION No.: 01 - Aug 20/14 Page: 55 6

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# @A340-500/600 SERVICE BULLETIN j After the inspection, restore the paint coating in accordance with the SRM 51-75-12 and SRM 51-23-11. NOTE : Refer to OIT 999.0130/06 ’pai nt system - best practices’. 7 If the largest repair ply is still not visible: a Remove the dust and dry the area in accordance with the SRM 51-77-11 Para 4.G. b Do a pulse thermography inspection to get the precise location and the size of the repair, refer to NTM 55-40-50. NOTE : The pulse thermography inspection indicates the outer skin repair ply geometry. The largest repair ply defines the boundary of the repair area. NOTE : In case of any findings (repair, damage, fluid ingress) during the pulse thermography inspection, save the images and send it together with the report sheet to AIRBUS. c Mark the boundary of the repair area, refer to Fig. A-GBEAA Sheet 02 and Fig. A-GBEAA Sheet 03
. d If fluid ingress has been detected during the pulse thermography inspection, refer to Subtask 555007-832-204-001 of this Service Bulletin. e Identify the booster areas in accordance with Fig. A-GBDAA Sheet 02 and Fig. A-GBDAA Sheet 03
. f If repairs in the booster areas up to 55000 mm 2 (85.25 sq.in.) have been detected, report the findings to AIRBUS. Use the report sheet Fig. A-GBHAA Sheet 02 and the rudder related sketches, refer to Fig. AGBHAA Sheet 03 and Fig. A-GBHAA Sheet 04
. <1> Restore the surface protection in accordance with the SRM 51-23-11. No further actions on these repairs in accordance with this Service Bulletin. g If repairs in the booster areas larger than 55000 mm 2 (85.25 sq.in.) have been detected, do the UT inspection around the repair in accordance with Subtask 555007-832-205-001 of this Service Bulletin. h If repairs not in the booster area have been detected, do the ELCH and/or UT inspection in accordance with Subtask 555007-832-205-001 of this Service Bulletin.

DATE: Feb 07/13 SERVICE BULLETIN No.: A340-55-5007 REVISION No.: 01 - Aug 20/14 Page: 56 6

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# @A340-500/600 SERVICE BULLETIN i After the inspection, restore the paint coating in accordance with the SRM 51-75-12 and SRM 51-23-11. NOTE : Refer to OIT 999.0130/06 ’pai nt system - best practices’. D. TEST None E. CLOSE-UP (1) Subtask 555007-942-201-001 - Close-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 29-00-00-863-801 Task 29-00-00-863-802 Task 29-00-00-863-803 55-40-00, Page Block 601 (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Remove the access platforms. (c) Close the circuit breakers as given in the inspection/check Close-up procedure, refer to AMM 55-40-00, Page Block 601. (d) Pressurize the Green Hydraulic System, refer to AMM Task 29-00-00-863-801. (e) Pressurize the Blue Hydraulic System, refer to AMM Task 29-00-00-863-802. (f) Pressurize the Yellow Hydraulic System, refer to AMM Task 29-00-00-863-803. (g) In the cockpit, remove all warning notices.

DATE: Feb 07/13 SERVICE BULLETIN No.: A340-55-5007 REVISION No.: 01 - Aug 20/14 Page: 57 6

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# @A340-500/600 SERVICE BULLETIN

**CONF ALL
Z326

MFR DESCR. SER. N ° CA CODE MFG DATE A/C PNNSA9117−63D XXXXXXXXXXXXX TS
−XXXX 

### A



## B

POSITION OF RUDDER S/N PLACARD 01
NOTE: USE A MIRROR OR FLEXIBLE ENDOSCOPE IF NECESSARY 01 

### B 

## A F_SB_555007_6_BAAA_01_02 Figure A-G BAAA - Sheet 01

Rudder SN identification DATE: Feb 07/13 SERVICE BULLETIN No.: A340-55-5007 REVISION No.: 01 - Aug 20/14 Page: 58 6

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# @A340-500/600 SERVICE BULLETIN

**CONF ALL
Z326



## A LH SHOWN RH SIMILAR 

### A

A

A B B C C F F

E E

D D

F_SB_555007_6_BBAA_01_01 Figure A-G BBAA - Sheet 01

Repair type identification DATE: Feb 07/13 SERVICE BULLETIN No.: A340-55-5007 REVISION No.: 01 - Aug 20/14 Page: 59 6

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

# @A340-500/600 SERVICE BULLETIN

**CONF ALL

OUTER SKIN WITH CORE CLOSING

OUTER SKIN AND CORE REPAIR WITHOUT CORE CLOSING

OUTER SKIN AND CORE REPAIR WITH CORE CLOSING

DELAMINATION AND CORE DAMAGE WITH CORE CLOSING (SRM 55
−41
−00 PAGE BLOCK 201 FIG.201/205) 

## A A

B B

C C (SRM 55
−41
−00 PAGE BLOCK 201 FIG.203/207)

(SRM 55
−41
−00 PAGE BLOCK 201 FIG.204/208/211)

(SRM 55
−41
−00 PAGE BLOCK 201 FIG.204/208/211)



## D D E E

F F OUTER SKIN WITHOUT CORE CLOSING (SRM 55
−41
−00 PAGE BLOCK 201 FIG. 212) (SRM 55
−41
− 13 PAGE BLOCK 201 FIG. 203) 

## EXAMPLES OF POSSIBLE DAMAGE TYPES (TAKEN FROM THE A340
−200/300 SRM PROCEDURES)

(SRM 55
−41
−00 PAGE BLOCK 201 FIG. 204/208/209/213/214) (SRM 55
−41
−00 PAGE BLOCK 201 FIG.204/208/211) (SRM 55
−41
− 13 PAGE BLOCK 201 FIG.204) (SRM 55
−41
− 13 PAGE BLOCK 201 FIG.206) BOTH SKIN AND CORE REPAIR WITH AND WITHOUT CORE CLOSING / REPAIR WITH ACCESS FROM ONE SIDE ONLY BOTH SKIN AND CORE REPAIR WITH AND WITHOUT CORE CLOSING / REPAIR WITH ACCESS FROM BOTH SIDE

F_SB_555007_6_BBAA_02_03 Figure A-G BBAA - Sheet 02

Repair type identification DATE: Feb 07/13 SERVICE BULLETIN No.: A340-55-5007 REVISION No.: 01 - Aug 20/14 Page: 60 6

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# @A340-500/600 SERVICE BULLETIN

**CONF ALL

REPAIR PROCEDURE 202 15.A., 15.C. 55
−41
−00 TEMPORARY REPAIR FOR LARGE DAMAGE. 5.B. 55
−41
− 13 55
−41
−00 REPAIR FOR ABRASIONS AND SCRATCHES IN THE RUDDER ZONE "A,B". 11.A., 11.C. 55
−41
−00 206 55
−41
−00 5.A. REPAIR FOR APEX STRIP IN THE RUDDER ZONE "D". 201 55
−41
− 13 202 5.E. 205 REPAIR FOR ABRASIONS AND SCRATCHES IN THE RUDDER ZONE "J".
REPAIR FOR DEBONDING WITHOUT CRACKS AND HOLES IN RUDDER ZONE "A,E,J,Q AND S". 55
−41
−00

REPAIR OF EDGE AT LOWER SHELL IN RUDDER ZONE "N". 55
−41
− 13 PARA. FIG.

19.A 210 CHAPTER TAKEN FROM A340
−200/300 SRM ISSUE: 01. OCT 2009

NOTE: REPAIRS ACCOMPLISHED IN ACCORDANCE WITH THE SRM PROCEDURES GIVEN IN THE LIST ABOVE, ARE NOT AFFECTED BY THIS SERVICE BULLETIN.

F_SB_555007_6_BCAA_01_03 Figure A-GBCAA - Sheet 01 Repair type identification - SRM list DATE: Feb 07/13 SERVICE BULLETIN No.: A340-55-5007 REVISION No.: 01 - Aug 20/14 Page: 61 6

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# @A340-500/600 SERVICE BULLETIN

**CONF ALL
Z326



## A B C A

F_SB_555007_6_BDAA_01_02 Figure A-GBDAA - Sheet 01 Booster area definition DATE: Feb 07/13 SERVICE BULLETIN No.: A340-55-5007 REVISION No.: 01 - Aug 20/14 Page: 62 6

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# @A340-500/600 SERVICE BULLETIN

**CONF ALL

DEFINITION OF BOOSTER AREA VALID FOR RUDDER LH SHOWN F55471015 

## B BR1 BR2 BR3BR4BR5 BR6 BR7 BR8A

956.0 mm (37.64 in) 3188.0 mm (125.51 in)

995.0 mm (39.17 in)

F_SB_555007_6_BDAA_02_02 Figure A-GBDAA - Sheet 02 Booster area definition DATE: Feb 07/13 SERVICE BULLETIN No.: A340-55-5007 REVISION No.: 01 - Aug 20/14 Page: 63 6

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# @A340-500/600 SERVICE BULLETIN

**CONF ALL

DEFINITION OF BOOSTER AREA

VALID FOR RUDDER RH SHOWN F55471015 

## C BR1 BR2 BR3 BR4 BR5 BR6 BR7 BR8A

956.0 mm (37.64 in) 3188.0 mm (125.51 in)

995.0 mm (39.17 in)

F_SB_555007_6_BDAA_03_02 Figure A-GBDAA - Sheet 03 Booster area definition DATE: Feb 07/13 SERVICE BULLETIN No.: A340-55-5007 REVISION No.: 01 - Aug 20/14 Page: 64 6

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# @A340-500/600 SERVICE BULLETIN

**CONF ALL
Z326



## A A

B E

B E

F_SB_555007_6_BEAA_01_02 Figure A-G BEAA - Sheet 01 Typical pulse thermography and ELCH/UT inspection DATE: Feb 07/13 SERVICE BULLETIN No.: A340-55-5007 REVISION No.: 01 - Aug 20/14 Page: 65 6

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# @A340-500/600 SERVICE BULLETIN

**CONF ALL

TYPICAL PULSE THERMOGRAPHY INSPECTION LH SHOWN RH SYMETRICAL 

## B BR1 BR2 BR3BR4BR5 BR6 BR7 BR8A



### C

D

F_SB_555007_6_BEAA_02_03 Figure A-G BEAA - Sheet 02 Typical pulse thermography and ELCH/UT inspection - Repair size assessment DATE: Feb 07/13 SERVICE BULLETIN No.: A340-55-5007 REVISION No.: 01 - Aug 20/14 Page: 66 6

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

# @A340-500/600 SERVICE BULLETIN

**CONF ALL

REPAIR SIZE = D2 x /4

100.0mm x 100.0mm

(3.93 in x 3.93 in) (15.50 sq.in) DAMAGE IN THE OUTER SKIN AND CORE
MAX. REPAIR PLY REPAIR PLY D

(110.0mm)2 x /4 = (4.33 in2 x /4)

ca. 10 000 mm2 = DAMAGE IN THE OUTER SKIN AND CORE MAX. REPAIR PLY

REPAIR PLIES

REPAIR SIZE = A x B

= 50.0mm x 200.0mm (1.97 in x 7.87 in) = OR
(15.50 sq.in) 10 000 mm2 = B

A EXAMPLE:

EXAMPLE: D = 110.0mm DIA


## C

D THE NEW CUTOUT SIZE FOR THE REPAIR IS THE 02 SIZE OF THE FORMER OUTER SKIN REPAIR PLY. 02

02

F_SB_555007_6_BEAA_03_01 Figure A-G BEAA - Sheet 03 Typical pulse thermography and ELCH/UT inspection - Repair size assessment DATE: Feb 07/13 SERVICE BULLETIN No.: A340-55-5007 REVISION No.: 01 - Aug 20/14 Page: 67 6

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

# @A340-500/600 SERVICE BULLETIN

**CONF ALL

TYPICAL ELCH/UT INSPECTION LH SHOWN RH SYMETRICAL INSPECTION AREA ELCH/UT SKIN THICKNESS 1.5mm (0.23 in): A=200.0mm (7.87 in) AROUND THE MAX. REPAIR PLY ELCH METHOD
GRID = 75.0mm x75.0mm (2.95 in x 2.95 in) SKIN THICKNESS 1.5mm (0.23 in): A=75.0mm (2.95 in) AROUND THE MAX. REPAIR PLY UT
−METHOD



## E BR1 BR2 BR3BR4BR5 BR6 BR7 BR8A



### F

MAX. REPAIR PLY
A

F_SB_555007_6_BEAA_04_03 Figure A-G BEAA - Sheet 04 Typical pulse thermography and ELCH/UT inspection - Boundary and grid of ELCH/UT inspections DATE: Feb 07/13 SERVICE BULLETIN No.: A340-55-5007 REVISION No.: 01 - Aug 20/14 Page: 68 6

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

# @A340-500/600 SERVICE BULLETIN

**CONF ALL
TYPICAL TRAILING EDGE ELCH INSPECTION

NOTE:

DISTANCE FROM EDGE 

## F 75.0 mm (2.95 in) 75.0 mm (2.95 in)

EXISTING SCREW

75.0 mm (2.95 in) 75.0 mm (2.95 in) 75.0 mm (2.95 in)

01 01

INSPECTION POINT ELCH TOOL TYPICAL TRAILING EDGE ELCH INSPECTION AROUND REPAIR AREA

75.0 mm (2.95 in) 75.0 mm (2.95 in) MAX. REPAIR PLY 02

02

SCREWS AND ELCH TOOL ARE NOT DRAWN TO SCALE 02 F_SB_555007_6_BEAA_05_05 Figure A-G BEAA - Sheet 05 Typical pulse thermography and ELCH/UT inspection - ELCH inspection grid DATE: Feb 07/13 SERVICE BULLETIN No.: A340-55-5007 REVISION No.: 01 - Aug 20/14 Page: 69 6

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

# @A340-500/600 SERVICE BULLETIN

**CONF ALL
Z326



## A B B A

F_SB_555007_6_BFAA_01_01 Figure A-GBFAA - Sheet 01 Core ventilation procedure DATE: Feb 07/13 SERVICE BULLETIN No.: A340-55-5007 REVISION No.: 01 - Aug 20/14 Page: 70 6

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

# @A340-500/600 SERVICE BULLETIN

**CONF ALL

MAX. RECTANGULAR REPAIR SIZE 100.0mm (3.94 in): DRILL HOLES THRU INNER AND OUTER SKIN. CAUTION: DO NOT DRILL THE OPPOSITE SHELL. NOTE:

03 01MIN. 90.0 mm(3.54 in)100.0 mm(3.94 in)

REPAIR SIZE DETECTED BY THERMOGRAPHY 02 02

APPLICABLE TO MAX. 6 HOLES IN A ROW TYPICAL CORE VENTING

IF REPAIR SIZE IS LARGER THAN 105 000mm2 (162.75 sq.in.), CONTACT AIRBUS FOR FURTHER INSTRUCTIONS

MAX. 100.0 mm (3.94 in)

03 

## C

DRILL 1 ROW IN THE MID OF THE REPAIR. IF THE RECTANGULAR REPAIR SIZE IS LARGER THAN 100.0mm (3.94 in), DRILL 2 ROWS AS SHOWN IN FIG. A
−GBFAA, SHEET 03. CONFIRM BY AN ADDITIONAL INSPECTION THAT THE DRILL 05 HOLE HAS PENETRATED THE INNER SKIN. (E.G. BY INSERTING A SUITABLE PIN DEEPER THAN NOMINAL PANEL THICKNESS, OR BY ILLUMINATION OF THE RUDDER FROM INSIDE THROUGH A HOLE IN THE SPAR AND VISUAL 

## A A 01 3.0 mm DIA

(0.12 in) 01 OUTER SKIN INNER SKIN OPPOSITE SHELL

MAX. REPAIR PLY 02 

### C D 05 

### A A

50.0 mm (1.97 in) TE
−SCREW



## B MAX. REPAIR PLY

INSPECTION THROUGH THE DRILL HOLE.) F_SB_555007_6_BFAA_02_04 Figure A-GBFAA - Sheet 02 Core ventilation procedure DATE: Feb 07/13 SERVICE BULLETIN No.: A340-55-5007 REVISION No.: 01 - Aug 20/14 Page: 71 6

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

# @A340-500/600 SERVICE BULLETIN

**CONF ALL

IF THE RECTANGULAR REPAIR SIZE IS LARGER THAN 100.0 mm

(3.94 in)

NOTE:

04 MIN. 90.0 mm (3.54 in)MIN. 90.0 mm(3.54 in)100.0 mm(3.94 in)

REPAIR SIZE DETECTED BY THERMOGRAPHY 02 MAX. REPAIR PLY 02

04



## D APPLICABLE TO MAX. 6 HOLES IN A SQUARE GRID

IF REPAIR SIZE IS LARGER THAN 105 000mm2 (162.75 sq.in.), CONTACT AIRBUS FOR FURTHER INSTRUCTIONS > 100.0 mm (3.94 in)

100.0 mm (3.94 in), DRILL 2 ROWS. F_SB_555007_6_BFAA_03_00 Figure A-GBFAA - Sheet 03 Core ventilation procedure DATE: Feb 07/13 SERVICE BULLETIN No.: A340-55-5007 REVISION No.: 01 - Aug 20/14 Page: 72 6

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

# @A340-500/600 SERVICE BULLETIN

**CONF ALL
Z326



## A B C A

F_SB_555007_6_BGAA_01_02 Figure A-GBGAA - Sheet 01 Rudder skin thickness identification DATE: Feb 07/13 SERVICE BULLETIN No.: A340-55-5007 REVISION No.: 01 - Aug 20/14 Page: 73 6

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

# @A340-500/600 SERVICE BULLETIN

**CONF ALL

< 1.5mm (0.059 in) VALID FOR RUDDER LH SHOWN SKIN THICKNESS > 1.5mm (0.059 in) SKIN THICKNESS NO INSPECTION BR1 BR2 BR3BR4 BR5 BR6 BR7 BR8A

1

F55471015 

## B

F_SB_555007_6_BGAA_02_02 Figure A-GBGAA - Sheet 02 Rudder skin thickness identification DATE: Feb 07/13 SERVICE BULLETIN No.: A340-55-5007 REVISION No.: 01 - Aug 20/14 Page: 74 6

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

# @A340-500/600 SERVICE BULLETIN

**CONF ALL

< 1.5mm (0.059 in) VALID FOR RUDDER RH SHOWN

SKIN THICKNESS > 1.5mm (0.059 in) SKIN THICKNESS NO INSPECTION BR1 BR2 BR3 BR4 BR5 BR6 BR7 BR8A

1

F55471015 

## C

F_SB_555007_6_BGAA_03_02 Figure A-GBGAA - Sheet 03 Rudder skin thickness identification DATE: Feb 07/13 SERVICE BULLETIN No.: A340-55-5007 REVISION No.: 01 - Aug 20/14 Page: 75 6

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

# @A340-500/600 SERVICE BULLETIN

**CONF ALL

REPAIR DETECTED WITH NIL DAMAGE NO REPAIR DETECTED PLEASE SEND REPORTING SHEET TO: AIRBUS CUSTOMER SERVICE STRUCTURE ENGINEERING DEPARTMENT SEES2 1 ROND POINT MAURICE BELLONTE 31707 BLAGNAC CEDEX FRANCE FAX +33 (0)5 61 93 36 14 Structure.sbinspectionresult@airbus.com REPAIR DETECTED WITH DAMAGE PLEASE SEND REPORTING SHEET TO: DEPARTMENT SEOE1/2/3 NOTE: ATTACH ALSO THE INITIAL PUSLE THERMOGRAPHY PHOTOS. PREVIOUS REPORTS PER SB55
−5007 REV00 FIGURE A
−GBHAA
−SHEET 01/02/03 ARE VALID AIRCRAFT MSN RUDDER S/N INSPECTION DATE FLIGHT CYCLES FC FLIGHT HOURS FH DATA

PULSE THERMOGRAPHY COMPLETE INSPECTION LH AND RH SIDE YES/NO

INSPECTION RESULT REPAIR DETECTED LH RH LIQUID INGRESS DETECTION DAMAGE CHECK UT −ELCH INDICATION SUMMARY RUDDER SIDE SHELLS SANDWICH REPAIR PULSE THERMOGRAPHY REPORT

F_SB_555007_6_BHAA_01_04 Figure A-GBHAA - Sheet 01 Report sheet and sketches - Pulse thermography report sheet DATE: Feb 07/13 SERVICE BULLETIN No.: A340-55-5007 REVISION No.: 01 - Aug 20/14 Page: 76 6

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

# @A340-500/600 SERVICE BULLETIN

**CONF ALL

PLEASE SEND REPORTING SHEET TO: AIRBUS CUSTOMER SERVICE STRUCTURE ENGINEERING DEPARTMENT SEES2 1 ROND POINT MAURICE BELLONTE 31707 BLAGNAC CEDEX FRANCE FAX +33 (0)5 61 93 36 14 Structure.sbinspectionresult@airbus.com FIGURE A
−GBHAA
−SHEET 01 / REPORT SHEET AND SKETCHES
−REPORT SHEET PREVIOUS REPORTS PER SB55
−5007 REV00 FIGURE A
−GBHAA
−SHEET 01 ARE VALID AIRCRAFT MSN RUDDER S/N RECORDS REVIEW DATE DATA

RECORDS STATUS REPAIR RECORDS COMPLETE SINCE ORIGINAL YES/NO

REPAIR SCHEME RUDDER FLIGHT CYCLES / FLIGHT HOURS REPAIR DATE LH OR RH SIDE SHELL SRM FIGURE 2XX (SRM 55
−41
−00 AND/OR 55
−41
− 13 PB201) DAMAGE SIZE (CIRCULAR) DIAMETER IN mm SUMMARY RUDDER SIDE SHELLS SANDWICH REPAIR RECORDS

SRM (STRUCTURAL REPAIR MANUAL) REPAIR PERFORMED REPAIR APPROVED BY LOCAL AIRWORTHINESS

DAMAGE SIZE (RECTANGULAR SHAPE) LENGTH AND WIDTH IN mm DAMAGE SIZE (mm2) REPAIR OUTER PLY SIZE (mm2) IF KNOWN FROM RECORDS LOCATION AS PER SRM 55
−41
−00 PB101 FIGURE 103 ZONE CODE.

SERVICE BULLETIN NO.: A330
−55
−5007 REVXX IN CASE OF MORE THAN 1 REPAIR, DUPLICATE THIS REPORTING SHEET (0 FLIGHT CYCLES) EIS ENTRY INTO SERVICE AUTHORITIES (NO AIRBUS APPROVAL)

F_SB_555007_6_BHAA_02_04 Figure A-GBHAA - Sheet 02 Report sheet and sketches - Repair records report sheet DATE: Feb 07/13 SERVICE BULLETIN No.: A340-55-5007 REVISION No.: 01 - Aug 20/14 Page: 77 6

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

# @A340-500/600 SERVICE BULLETIN

**CONF ALL 

## Rudder Side Shell (Show damage location, size and type.) 

## Sandwich Repair Inspection F55471015

Damage location Damage description / type Damage size mm2 / sq.in. Valid for rudder:

NOTE: FOR THE DAMAGE LOCATION, MARK THE AREA AND IDENTIFY WITH A NUMBER. 01 01



## LH

BR1 BR2 BR3 BR4 BR5 BR6 BR7 BR8A

F_SB_555007_6_BHAA_03_03 Figure A-GBHAA - Sheet 03 Report sheet and sketches DATE: Feb 07/13 SERVICE BULLETIN No.: A340-55-5007 REVISION No.: 01 - Aug 20/14 Page: 78 6

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

# @A340-500/600 SERVICE BULLETIN

**CONF ALL 

## Rudder Side Shell (Show damage location, size and type.) 

## Sandwich Repair Inspection

Damage location Damage description / type Damage size mm2 / sq.in. Valid for rudder:

NOTE: FOR THE DAMAGE LOCATION, MARK THE AREA AND IDENTIFY WITH A NUMBER. 01 01 

## RH F55471015

BR1 BR2 BR3 BR4 BR5 BR6 BR7 BR8A

F_SB_555007_6_BHAA_04_01 Figure A-GBHAA - Sheet 04 Report sheet and sketches DATE: Feb 07/13 SERVICE BULLETIN No.: A340-55-5007 REVISION No.: 01 - Aug 20/14 Page: 79 6

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

# @A340-500/600 SERVICE BULLETIN

**CONF ALL
Z326



## A B B A

F_SB_555007_6_BJAA_01_02 Figure A-GBJAA - Sheet 01 GFRP area location DATE: Feb 07/13 SERVICE BULLETIN No.: A340-55-5007 REVISION No.: 01 - Aug 20/14 Page: 80 6

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

# @A340-500/600 SERVICE BULLETIN

**CONF ALL

VALID FOR RUDDER LH SHOWN RH SYMMETRICAL F55471015 

## B BR1 BR2 BR3BR4BR5 BR6 BR7 GFRP AREA

CFRP AREA 1012.0 mm (39.84 in) BR8A
561.0 mm (22.09 in)

F_SB_555007_6_BJAA_02_02 Figure A-GBJAA - Sheet 02 GFRP area location DATE: Feb 07/13 SERVICE BULLETIN No.: A340-55-5007 REVISION No.: 01 - Aug 20/14 Page: 81 6

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

# @A340-500/600 SERVICE BULLETIN

**CONF ALL CHECK THE RUDDER RECORDS IF REPAIRS (AIRBUS RAS , SRM AND OTHER )

NO YES

PERFORM PULSE THERMOGRAPHY INSPECTION ON COMPLETE REPORT THE INFORMATION TO AIRBUS. 01

PERFORMED SINCE RUDDER EIS ?

REPAIR DETECTED, WHICH

NO

YES REPAIR
YES NO

REPORT THE INFORMATION TO AIRBUS. PERFORM ELCH AND/OR UT AROUND THE IDENTIFIED

NO FURTHER ACTION REQUIRED IN ACCORDANCE WITH THIS SB. REFER TO FLOW CHART 2 FOR ACTIONS ON IDENTIFIED REPAIRS. COMPLETE REPAIR RECORDS AVAILABLE SINCE RUDDER EIS ?

REPAIRS. SIDE SHELLS TO IDENTIFY REPAIRS: MARK THE REPAIRS.

YES
REPAIRS IN THE BOOSTER AREA REPAIR SIZE 55000mm2 LARGER THAN 03 (85.25 sq.in.)

NO ARE RECORDED SINCE RUDDER EIS AND 04 05

06 OR NOT IN THE BOOSTER AREA. 03 REPORT UNDOCUMENTED RUDDER S/N LIST TO AIRBUS SEES2 TO GET RELATED RUDDER MANUFACTURING REWORK DATA 07

IS NOT MANUFACTURING REWORK ? 08 12 FOR PAINT THICKNESS IDENTIFICATION REFER TO FLOW CHART 5

FLUID

YES NO NO FURTHER ACTIONS. CONTINUE WITH ACTIONS AS PER FLOW CHART 3. INGRESS DETECTED REPAIR TYPE INSPECTED IN ACCORDANCE WITH THE SB. 02 IDENTIFIED TO BE REPORT THE INFORMATION TO AIRBUS.

PERFORM PULSE THERMOGRAPHY ON REPAIR LOCATION TO PRECISE LOCATION AND SIZE. YES NO

NO YES

REPORT THE INFORMATION TO AIRBUS. MARK THE REPAIRS.

REPAIRS IN THE BOOSTER AREA REPAIR SIZE 55000mm2 LARGER THAN 03 (85.25 sq.in.) 06 OR NOT IN THE BOOSTER AREA. 03 12 FOR PAINT THICKNESS IDENTIFICATION REFER TO FLOW CHART 5

AND PERFORM LOCAL SANDING ON TOP AND

REPAIR PLY OF THE REPAIR LARGEST VISIBLE? YES

NO 28 AROUND THE PEPAIR UP TO PRIMER.

PERFORM LOCAL SANDING ON TOP AROUND THE REPAIR 24 25 UP TO ADHESIVE.

REPAIR PLY OF THE REPAIR LARGEST VISIBLE? YES OR

NO 26 LOCAL PAINT THICKNESS IDENTIFICATION 27

MARK REPAIR SIZE ON SURFACE 22 23 25

F_SB_555007_6_FAAA_01_05 Figure A-GFAAA - Sheet 01

Flow Chart - Flow Chart 1 DATE: Feb 07/13 SERVICE BULLETIN No.: A340-55-5007 REVISION No.: 01 - Aug 20/14 Page: 82 6

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

# @A340-500/600 SERVICE BULLETIN

**CONF ALL ACTIONS ON IDENTIFIED REPAIRS
DAMAGE DETECTED NO YES

PROVIDE DETAILED DAMAGE REPORT AND REPAIR SIZE 10000mm2, (15.50 sq.in.)
−

PROVIDE DETAILED INFORMATION TO AIRBUS AVAILABLE. PERFORM REPETITIVE ELCH AND/OR UT INSPECTION AROUND THE IDENTIFIED REPAIR. PERFORM CORE VENTING THROUGH INNER SKIN, IN ACCORDANCE WITH VENTING SCHEME. PERFORM CORE VENTING THROUGH INNER SKIN, IN ACCORDANCE WITH VENTING SCHEME. OR

ON IDENTIFIED REPAIR DETAILED INFORMATION ON IDENTIFIED REPAIR IF REPORT TO AIRBUS AND FOLLOW THEIR INSTRUCTIONS. FINDINGS YES NO REPORT THE RESULTS AND PLANNED TERMINATING ACTION ON IDENTIFIED

REPAIR IN ACCORDANCE WITH SRM AT THE IDENTIFIED REPAIR LOCATION. REPAIR IN ACCORDANCE WITH SRM AND WITH ADDITIONAL INSTRUCTIONS FROM AIRBUS. REPLACE AFFECTED RUDDER SHELL OR REPLACE THE RUDDER.

REFER TO FIGURE A
−GFAAA, SHEET 06. NOTE: 09 09 REPAIR SIZE 09 REPAIR SIZE 09 REPAIR SIZE 09

10 10 11 TO AIRBUS SEOE 1/2/3 OR TERMINATING ACTION 20000mm2, (31.00 sq.in.). 20000mm2, (31.00 sq.in.) 80000mm2, (124.00 sq.in.). − 80000mm2, (124.00 sq.in.). 10000mm2, (15.50 sq.in.).

NO FURTHER ACTION REQUIRED IN ACCORDANCE WITH THIS SB. AIRTAC AND FOLLOW PERFORM CORE VENTING THROUGH INNER SKIN, IN ACCORDANCE WITH VENTING SCHEME.

REPAIR TO AIRBUS SBO 5, COPY SEES2 REPORT THE RESULTS AND PLANNED TERMINATING ACTION ON IDENTIFIED REPORT THE RESULTS AND PLANNED TERMINATING ACTION ON IDENTIFIED

TERMINATING ACTION

REPAIR SIZE 30000mm2, (46.50 sq.in.). REPAIR SIZE 30000mm2, (46.50 sq.in.).

NO FURTHER ACTION REQUIRED IN ACCORDANCE WITH THIS SB. REFER TO FIGURE A
−GBEAA. THEIR INSTRUCTIONS REPAIR TO AIRBUS SBO 5, COPY SEES2 REPAIR TO AIRBUS SBO 5, COPY SEES2

19 19

F_SB_555007_6_FAAA_02_06 Figure A-GFAAA - Sheet 02

Flow Chart - Flow Chart 2 DATE: Feb 07/13 SERVICE BULLETIN No.: A340-55-5007 REVISION No.: 01 - Aug 20/14 Page: 83 6

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

# @A340-500/600 SERVICE BULLETIN

**CONF ALL

ACTIONS ON DETECTED FLUID INGRESS.

LOCAL SINGLE SPOT FLUID INGRESS

1500 mm2, (2.33 sq.in.) AND 5000 mm2, (7.75 sq.in.) LOCAL SINGLE SPOT FLUID INGRESS

1500 mm2, (2.33 sq.in.) LOCAL SPOT FLUID INGRESS 5000 mm2, (7.75 sq.in.)

DRAIN BY CORE VENTING.

REPORT TO AIRBUS SEOE 1/2/3 OR AIRTAC AND FOLLOW THEIR INSTRUCTIONS. REPORT TO AIRBUS.

NO FURTHER ACTION REQUIRED IN ACCORDANCE WITH THIS ISB. REPETITIVE THERMOGRAPHY RE
−INSPECTION.

DO THE REPAIR. ACTIONS ON DETECTED FLUID INGRESS.
PERFORM ELCH AND/OR UT AROUND THE IDENTIFIED FLUID INDICATION
DAMAGE DETECTED YES NO

THAN 5 SPOTS PER

NO REPORT TO AIRBUS SEOE 1/2/3 OR AIRTAC AND FOLLOW THEIR INSTRUCTIONS. MORE SIDE SHELL YES

NO DETECTED THAN 5 SPOTS PER SIDE SHELL YES MORE DETECTED NO

F_SB_555007_6_FAAA_03_06 Figure A-GFAAA - Sheet 03

Flow Chart - Flow Chart 3 DATE: Feb 07/13 SERVICE BULLETIN No.: A340-55-5007 REVISION No.: 01 - Aug 20/14 Page: 84 6

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

# @A340-500/600 SERVICE BULLETIN

**CONF ALL INSPECT THE RUDDER SIDE SHELL

KNOWN IN THE YES NO
PERFORM ON REPAIR LOCATION AND

TYPE A
−A YES NO IN CASE OF FINDINGS,

TAP TEST INSPECTION

OR WOODPECKER ALL OTHER REPAIR TYPES: PERFORM ELCH IDENTIFIED REPAIRS

CONTINUE WITH ACTIONS IN FLOW CHART 2 UPPER GFRP AREA

GFRP AREA

REPAIRS

PULSE THERMOGRAPHY INSPECTION MARK THE REPAIR
REPAIR REPORTED
PERFORM INSPECTION AND/OR UT AROUND THE PERFORM ON THE COMPLETE PULSE THERMOGRAPHY INSPECTION GFRP AREA

TAP TEST INSPECTION OR WOODPECKER INSPECTION PERFORM ON THE COMPLETE GFRP AREA MARK THE REPAIRS

CORE DISBONDING YES
NO SKIN TO IDENTIFIED

ALL OTHER REPAIR TYPES: PERFORM ELCH IDENTIFIED REPAIRS AND/OR UT AROUND THE

NOTE: REFER TO FIGURE A
−GFAAA, SHEET 06. 18 18 WHICH ARE NOT MANUFACTURING REWORKS 20 21

F_SB_555007_6_FAAA_04_03 Figure A-GFAAA - Sheet 04

Flow Chart - Flow Chart 4 DATE: Feb 07/13 SERVICE BULLETIN No.: A340-55-5007 REVISION No.: 01 - Aug 20/14 Page: 85 6

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

# @A340-500/600 SERVICE BULLETIN

**CONF ALL PULSE THERMOGRAPHY PAINT

OPERATOR IS SURE THAT THE NO GFRP
−AREA 400.00 microns THICKNESS LIMITATION

RUDDER PAINT THICKNESS IS BELOW THE GIVEN LIMITS YES

APPLY PAINT THICKNESS MEASUREMENT TOOL

NO

LOCAL PAINT REMOVAL RUDDER PAINT THICKNESS IS BELOW THE GIVEN

LIMITS YES

CONTINUE WITH ACTIONS DEFINED IN FLOW CHART 1 PAINT RESTORATION IS REQUIRED AFTER PULSE THERMOGRAPHY AND/OR ELCH/UT INSPECTION NOTE: 13 REFER TO FIGURE A
− FAAA, SHEET 06 13 14

16

15 17 PAINT RESTORATION IS REQUIRED AFTER PULSE THERMOGRAPHY AND/OR ELCH/UT INSPECTION CFRP
−AREA 800.00 microns OR 400.00 microns BELOW DECAL FOIL

F_SB_555007_6_FAAA_05_05 Figure A-GFAAA - Sheet 05

Flow Chart - Flow Chart 5 DATE: Feb 07/13 SERVICE BULLETIN No.: A340-55-5007 REVISION No.: 01 - Aug 20/14 Page: 86 6

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

# @A340-500/600 SERVICE BULLETIN

**CONF ALL
SEE AIRBUS LIST WITH A/C MSN, RUDDER S/N SEE AIRBUS DEFINITION OF REPAIR TYPES AFFECTED BY THE ISB INSPECTION. REFER TO FIGURE A
−GBBAA. SEE AIRBUS BOOSTER DEFINITION. NOTE: 01 02 03 AND RAS NUMBER, REFER TO FIGURE A
−GBCAA.

IF AN AIRCRAFT LISTED IN THE SB EFFECTIVITY HAS A REPAIR EMBODIED THAT IS NOT OF AIRBUS ORIGIN, 04 AND WHICH AFFECTS THE CONTENT OF THIS SB, THE APPROVAL BY ITS AIRWORTHINESS AUTHORITY FOR ANY ADAPTATION NECESSARY BEFORE THIS ACTION IS NOT NECESSARY, IF THE INFORMATION HAS BEEN ALREADY SENT TO AIRBUS IN ACCORDANCE 05 NEXT STEP. REFER TO FIGURE A
−GBDAA.

OPERATOR IS RESPONSIBLE FOR OBTAINING THE INCORPORATION OF THE SB. WITH THE OIT SE 999.0071/10 CONTINUE WITH THE REPAIR SIZE DEFINED BY THE LARGEST REPAIR PLY. 06 07 BASED ON PROVIDED AIRBUS EVALUATION OF RUDDER 08 S/N MANUFACTURING REWORK DATA.

FOR GFRP
−AREA INSPECTION REFER TO FLOW CHART 4 12 REPAIR SIZE DEFINED BY THE LARGEST REPAIR PLY. PENDING AVAILABILITY OF SRM IMPROVED REPAIR, AIRBUS IS TO BE CONTACTED FOR INSTRUCTIONS. SIDE SHELL REPLACEMENT CAN BE DONE ONLY AT THE AIRBUS STADE FACILITY. 09 10 11 REFER TO FIGURE A
−GBEAA. THE NEW REPAIR CUTOUT IS EQUAL TO 19 THE LARGEST OUTER SKIN REPAIR PLY. REFER TO FIGURE A
−GBBAA 18
IN CASE OF FLUID INGRESS REFER TO 20 FLOW CHART 3 FOR FURTHER INSTRUCTIONS FOR PAINT THICKNESS IDENTIFICATION REFER TO 21 FLOW CHART 5

13 PRIOR TO THE APPLICATION OF THE PULSE THERMOGRAPHY METHOD NTM 55
−40
−50 THE OPERATOR HAS TO CHECK THE SIDE SHELL PAINT THICKNESS. IT IS THE OPERATORS RESPONSIBILITY TO ENSURE THAT THE RUDDER SIDE SHELL PAINT THICKNESS IS BELOW THE GIVEN LIMITS. PLEASE CONSIDER THE INFORMATION FOR PAINT RESTORATION PROVIDED WITH THE OIT 999.0130/06 DATED 21 NOV 2006. SRM 51
−75
− 11 RECOMMENDS ABRADING COMPOSITE SURFACE UP TO THE FIRST PRIMER COATING IN ORDER TO AVOID SURFACE DAMAGE OF THE COMPOSITE. IN CASE OF A SMOOTH AND EVEN PAINT THICKNESS DISTRIBUTION FIG. A
−GABAA PROVIDE GUIDANCE MATERIAL ABOUT A FEASIBLE PAINT BORER LOCATION DISTRIBUTION OVER THE SIDE SHELL. IN CASE PAINT REMOVAL LARGER THAN 2m2 IS REQUIRED IT IS RECOMMENDED TO REMOVE THE RUDDER FROM THE A/C.

14 15 16 17

CLEAN THE PREVIOUS REPAIR AREA. 22 REFER TO SRM 51
−77
− 11 PARA 4.E. PERFORM A LOCAL MECHANICAL SANDING A STEP BY STEP BASIS UP TO INITIAL BASIC PRIMER LAYER. AS PER SRM 51
−75
− 11 PARA 3.D. ON 23 ON TOP/AROUND THE REPAIR NO VISIBLE REPAIR: USING ABRASIVE CLOTH GRADE 100, 220, 280, 400. MECHANICAL SANDING ON A STEP BY STEP BASIS 24 CONTINUE LOCAL SANDING UP TO PORE FILLER/ADHESIVE. REFER TO SRM 51
−77
− 11 PARA 4.D. ENSURE NO DAMAGE TO CFRP OR GFRP BASE MATERIAL. 25

IF THE LARGEST REPAIR PLY IS NOT VISIBLE, BEYOUND THE INITIAL DETECTED REPAIR PATCH. 26 CONTINUE LOCAL SANDING ON AND AROUND THE REPAIR WITH A RADIUS APPROX. 50.0mm (1.97in) USE PAINT BORER TO ASSESS LOCAL PAINT SCHEME, THICKNESS AND INITIAL BASIC PRIMER 27 PRIOR SANDING. USE ON TOP OF REPAIR AND BESIDE REPAIR LOCATION. MAX. 1m2 (10.76 sq.ft.) SANDED AREA PER LOCAL REPAIR IS ALLOWED. 28 SRM 51
−77
− 10 AND SEND A DETAILED REFERENCE REPORT TO SEOE DEPARTMENT. IN CASE OF DAMAGE, PERFORM ASSESSMENT AS PER IT IS THE OPERATOR’S RESPONSIBILITY TO ENSURE THAT THE STRUCTURAL SIDE SHELL OUTER SKIN PLY (CFRP OR GFRP) IN ACCORDANCE TO THE DESIGN DRAWING IS NOT DAMAGED DURING THE LOCAL SANDING PROCESS. REMARK: IN MOST OF THE RUDDER SURFACE THE OUTER SKIN CONSISTS ONLY OF ONE CFRP OR GFRP PLY! IN CASE OF SANDING DAMAGE IMMEDIATE REPAIR BEFORE NEXT FLIGHT IS REQUIRED. AN AREA DAMAGED BY THE LOCAL SANDING COMBINED WITH AN EXISTING REPAIR CAN LEAD TO A NON
− REPAIRABLE SIZE AND SUBSEQUENT SIDE SHELL REPLACEMENT! REWORK COMPLETE DATA. AIRBUS MUST BE CONTACTED FOR MANUFACTURING

F_SB_555007_6_FAAA_06_01 Figure A-GFAAA - Sheet 06 Flow Chart DATE: Feb 07/13 SERVICE BULLETIN No.: A340-55-5007 REVISION No.: 01 - Aug 20/14 Page: 87 6

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# @A340-500/600 SERVICE BULLETIN

**CONF ALL

Closing of ventilation holes in outer skin Method 1 −Application of a bonded cover NOTE: This repair needs to be re
−inspected. Correct cover application has to be ensured by frequent detailed visual inspection during the application period at intervals not exceeding 900 FH. 1. Apply high speed tape over the ventilation hole, refer to Chapter 51
−77
− 12 Paragraph 2. Method 2 −Application of laminated cover NOTE: This repair needs no re
−inspection. 2. Prepare the repair area, refer to Chapter 51
−77
− 11 Paragraph 4.M.(2)., apply only step 1 to 2 and 10 to 17. 3. Protect the area adjacent to the repair area with flash tape (Material No. 05RFB1), refer to Chapter 51
−77
− 11, Paragraph 3.B.(2). 4. Prepare the laminating resin (Material No. 13EBC1), refer to Chapter 51
−77
− 11, Paragraph 6.B.(2) and 4.A.(3). 5. Prepare the repair plies (MIL
−C
−9084C TYPE VIIIA or B
−style 7781 dry glass fabric), refer to Chapter 51
−77
− 11, Paragraph 4.H. For ply dimensions and orientation refer to Figure 1. NOTE: Round all corners with radii 12mm (0.5 in.) minimum. 6. Prepare the laminating resin, refer to Chapter 51
−77
− 11, Paragraph 6.B.(2) and 4.A.(3). 7. Apply repair plies to the repair area as shown in Figure 1, refer to Chapter 51
−77
− 11, Paragraph 5.A. 8. If the repair cure shall be accelerated by heat:

−Install the vaccum bag, refer to Chapter 51
−77
− 11, Paragraph 5.D.(1), respect modificatons shown on Figure 2 and the heating equipment.

−Allow repair to cure under vacuum pressure, refer to Chapter 51
−77
− 11, Paragraph 5.E., use 22 in. of hg (560 mm of hg or 75 Kpa) minimum. Let the resin gel for one hour at room temperature, then cure for 4 hours at 60 C, refer to Chapter 51
−77
− 11, Paragraph 5.E.

−Remove the vacuum bag and the heating equipment.

−Continue with step 10. 9. If the repair cure shall be performed at room temperature:

−Install the vacuum bag, refer to Chapter 51
−77
− 11, Paragraph 5.D.(1) and respect modifications shown on Figure 2.

−Allow repair to cure under vacuum pressure, refer to Chapter 51
−77
− 11, Paragraph 5.E., use 22 in. of hg (560 mm of hg or 75 Kpa) minimum. Let the resin cure for six hours at room temperature or perform resin gelation test outside the repair area, after resin gelation perform cure for two hours (the latter approach must be applied if RT is below 18 C (65 F)).

−Remove the vacuum bag and continue with step 10 during the next stop. 10. Remove the flash tape. Ensure that the glass ply is correctly located and cured, refer to Chapter 51
−77
− 10, Paragraph 5. 11. Remove any resin remnants from the border area of the glass ply, use abrasive paper. Start with 280 grade and finish with 400 grade. WARNING: CLEANING AGENT (MATERIAL NO. 08BBF1 or 08BBU9) IS DANGEROUS. 12. Clean the repair area with cleaning agent (Material No. 08BBF1 or 08BBU9), refer to Chapter 51
− 77
− 10, Paragraph 4.E.(1)(a). 13. Restore the surface protection, refer to Chapter 51
−75
− 12.

F_SB_555007_6_AAAA_01_03 Figure A-GAAAA - Sheet 01 Closing of ventilation holes DATE: Feb 07/13 SERVICE BULLETIN No.: A340-55-5007 REVISION No.: 01 - Aug 20/14 Page: 88 6

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# @A340-500/600 SERVICE BULLETIN

**CONF ALL



## Figure 1
−Ply lay
−up Ply 2 0/90 42 x 42mm Ply 1 45 30 x 30mm Ply 3 45 54 x 54mm

GLASS PLY FLASH TAPE NON PERFORATING PARTING FILM RUBBER CAUL PLATE BREATHER DRY GLASS FABRIC OR PEEL PLY VACUUM GAGE VACUUM SOURCE VACUUM BAG FILM

VACCUM BAG SEALANT TAPE NOTE: RUBBER CAUL PLATE IS MANDATORY, 01 01

REFER TO CHAPTER 51
−77
− 11, PARAGRAPH 3.C. 

## Figure 2
−Bagging for curing process
F_SB_555007_6_AAAA_02_00 Figure A-GAAAA - Sheet 02 Closing of ventilation holes DATE: Feb 07/13 SERVICE BULLETIN No.: A340-55-5007 REVISION No.: 01 - Aug 20/14 Page: 89 6

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# @A340-500/600 SERVICE BULLETIN

**CONF ALL PAINT THICKNESS MEASUREMENT USING THE PAINT BORER ON THE RUDDER SIDE SHELL

THE PAINT THICKNESS MUST BE DETERMINED FOR A CORRECT SETTING OF THE PULSE THERMOGRAPHY INSPECTION PARAMETERS. IF THE THICKNESS IS UNKNOWN DETERMINE THE THICKNESS WITH THE PAINT BORER. DESCRIPTION 1. GENERAL A. THIS PROCEDURE CONTAINS THE INSPECTION PROCEDURE DESCRIBING PAINT THICKNESS MEASUREMENT USING THE PAINT BORER ON THE RUDDER SIDE SHELL.

PROCEDURE 1 TASK SUPPORTING DATA A. AREA OF APPLICABILITY ALL RUDDER INSPECTED WITH NTM 55
−40
−50 B. DESCRIPTION OF POSSIBLE DAMAGE

THE PAINT THICKNESS MUST BE DETERMINED FOR A CORRECT SETTING OF THE PULSE THERMOGRAPHY INSPECTION PARAMETERS. IF THE THICKNESS IS UNKNOWN DETERMINE THE THICKNESS WITH THE PAINT BORER. C. JOB SETUP INFORMATION

(1) TOOLING PREFERRED TOOL: PAINT BORER 518MC WITH THE DRILLS IN TABLE 1 ALTERNATIVE TOOL: PAINT BORER 518 OR PAINT BORER 518S WITH THE DRILLS IN TABLE 1 ADDITIONAL DOCUMENT: OPERATING MANUAL PAINT BORER

TABLE 1 : DRILLS F_SB_555007_6_ABAA_01_04 Figure A-GABAA - Sheet 01 Paint borer instructions DATE: Feb 07/13 SERVICE BULLETIN No.: A340-55-5007 REVISION No.: 01 - Aug 20/14 Page: 90 6

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# @A340-500/600 SERVICE BULLETIN

**CONF ALL

2 PROCEDURE:
1. PREPARE THE PAINT BORER ACCORDING TO THE OPERATING

1. PLACE THE PAINT BORER ON THE AREA, WHERE THE THICKNESS OF THE RUDDER PAINT HAS TO BE MEASURED, SEE FIG. A
−GABAA SHEET 3+4 2. DO THE DRILLING AND THE PAINT THICKNESS MEASUREMENT ACCORDING PAINT BORER OPERATING INSTRUCTIONS, REFER ALSO CAUTION: DO NOT DRILL DEEPLY INTO THE BASE MATERIAL (CFRP OR GFRP). ONLY A TINY BASE MATERIAL SPOT IS ENOUGH TO MEASURE THE PAINT THICKNESS, REFER TO FIG. A
−GABAA SHEET 5+6 3. APPLY A CONTRAST MARK (WITH A NON PERMANENT MARKER PEN) ON THE THE SPOT OF MEASUREMENT. IF THE RUDDER PAINT IS LIGHT (E.G. YELLOW, WHITE ...), USE A DARK (BLACK) PEN TO ENHANCE CONTRAST OF THE TOP COATING, IN CASE OF A DARK TOP COAT USE A LIGHT (WHITE) PEN. SEE A. PREPARATION FOR INSPECTION

B. INSTRUMENT ADJUSTMENT 1. NO C: INSPECTION PROCEDURE INSTRUCTIONS.

4. RECORD ALL THE MEASURED PAINT THICKNESS VALUES FOR THE PULSE THERMOGRAPHY INSPECTION. 5. AFTER MEASUREMENT SEAL THE SPOT WHERE DRILLED
−REFER TO SRM 51
−75
− 10. FIG. A
−GABAA SHEET 7+8 TO FIGURE A
−GABAA SHEET 3
−8

−IF THE LAYER THICKNESS IS NOT KNOWN,

INITIALLY USE A DRILL WITH 20
−2000 m ( CUT ANGLE: 45°) TO BRING THE FULL SECTION INTO VIEW; CHANGE TO 10
− 1000 m (CUT ANGLE: 26.6°) IF THICKNESS TURNS OUT TO BE 1000 m OR LESS μ μ μ CAUTION: IT IS IMPORTANT TO HAVE THE ABOVE SPECIFIED DRILLS AVAILABLE. CONTACT DRILL SUPPLIER IF THE CUTTING ANGLE AND DRILL NUMBERING CAUTION: DO NOT USE ULTRASONIC OR EDDY CURRENT BASED PAINT THICKNESS MEASUREMENT DEVICES, AS EDDY CURRENT ONLY WORKS ON METALLIC AND FOR ULTRASONIC BASED DEVICES THE NUMBER OF POSSIBLE PAINT LAYERS IS TOO HIGH TO GET RELIABLE RESULTS. IS UNKNOWN.

F_SB_555007_6_ABAA_02_05 Figure A-GABAA - Sheet 02 Paint borer instructions DATE: Feb 07/13 SERVICE BULLETIN No.: A340-55-5007 REVISION No.: 01 - Aug 20/14 Page: 91 6

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# @A340-500/600 SERVICE BULLETIN

**CONF ALL

Z326



## A A

LH SHOWN RH SIMILAR 

### C D E

B D E CFRP AREA GFRP AREA

F_SB_555007_6_ABAA_03_01 Figure A-GABAA - Sheet 03 Paint borer instructions DATE: Feb 07/13 SERVICE BULLETIN No.: A340-55-5007 REVISION No.: 01 - Aug 20/14 Page: 92 6

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# @A340-500/600 SERVICE BULLETIN

**CONF ALL



## D E PAINT SYSTEM DIFFERENT LAYERS (E.G. FILLER, PRIMER, TOP COAT, ...)

CFRP

HONEYCOMB CORE d

NOTE: DRILL HOLE 01 01

d = PAINT SYSTEM THICKNESS SPOT DRILLING

DETERMINATION OF PAINT THICKNESS PAINT SYSTEM DIFFERENT LAYERS (E.G. FILLER, PRIMER, TOP COAT, ...)

GFRP

HONEYCOMB CORE d 01 

## B

C F

G

F_SB_555007_6_ABAA_04_01 Figure A-GABAA - Sheet 04 Paint borer instructions DATE: Feb 07/13 SERVICE BULLETIN No.: A340-55-5007 REVISION No.: 01 - Aug 20/14 Page: 93 6

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# @A340-500/600 SERVICE BULLETIN

**CONF ALL



## F 1) NOT DRILLED DEEP

ENOUGH 2) GOOD DRILLED DEPTH (TINY CFRP SPOT) 3) DRILLED TO DEEP (BIG CFRP SPOT)

7) DRILLED TO DEEP

(DAMAGE OF THE HONEYCOMB 6) DRILLED TO DEEP

(BIG CFRP SPOT) 5) GOOD DRILLED

DEPTH (TINY 4) NOT DRILLED

DEEP ENOUGH CFRP SPOT) CORE)

F_SB_555007_6_ABAA_05_00 Figure A-GABAA - Sheet 05 Paint borer instructions DATE: Feb 07/13 SERVICE BULLETIN No.: A340-55-5007 REVISION No.: 01 - Aug 20/14 Page: 94 6

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# @A340-500/600 SERVICE BULLETIN

**CONF ALL

8) NOT DRILLED DEEP

ENOUGH 9) NOT DRILLED DEEP ENOUGH 10) GOOD DRILLED DEPTH 11) DRILLED TOO DEEP (BIG GFRP SPOT)

12) GOOD DRILLED DEPTH (DAMAGE OF THE 13) DRILLED TOO DEEP (TINY GFRP SPOT) 14) DRILLED TOO DEEP (DAMAGE OF THE (TINY GFRP SPOT)

HONEYCOMB CORE) HONEYCOMB CORE) 

## G

F_SB_555007_6_ABAA_06_00 Figure A-GABAA - Sheet 06 Paint borer instructions DATE: Feb 07/13 SERVICE BULLETIN No.: A340-55-5007 REVISION No.: 01 - Aug 20/14 Page: 95 6

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# @A340-500/600 SERVICE BULLETIN

**CONF ALL

F_SB_555007_6_ABAA_07_00 Figure A-GABAA - Sheet 07 Paint borer instructions DATE: Feb 07/13 SERVICE BULLETIN No.: A340-55-5007 REVISION No.: 01 - Aug 20/14 Page: 96 6

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# @A340-500/600 SERVICE BULLETIN

**CONF ALL

BR1 BR2 BR3

BR4 BR5 BR6 BR7 200.0mm (7.87in.) AFT OF BR7 RIVET CENTER

200.0mm (7.87in.) FWD OF HOIST POINT CENTER LINE PROPOSAL: 1SPOT IN GFRP AREA 6SPOTS IN CFRP AREA 

### A

B

C 

## A

B

C D 200.0mm (7.87in.) FWD OF HOIST POINT CENTER LINE



## D 600.0mm (23.62in.) 600.0mm (23.62in.)

200.0mm (7.87in.) FROM BR2 RIVET CENTER LINE

F_SB_555007_6_ABAA_08_02 Figure A-GABAA - Sheet 08 Paint borer instructions DATE: Feb 07/13 SERVICE BULLETIN No.: A340-55-5007 REVISION No.: 01 - Aug 20/14 Page: 97 6

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# @A340-500/600 SERVICE BULLETIN REPORTING SHEET 

### TITLE: STABILIZERS - RUDDER SIDE SHELL SANDWICH REPAIR INSPECTION 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: Feb 07/13 SERVICE BULLETIN No.: A340-55-5007 REVISION No.: 01 - Aug 20/14 Page: 1 6

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# @A340-500/600 SERVICE BULLETIN QUALITY PERCEPTION FORM Use this form to tell us what is your perception of the quality of this Service Bulletin. The reported data that you provide us will be used to analyse areas of difficulties and to take corrective action to further improve the quality of our Service Bulletins. We thank you for the time you have taken in completing this form. (Please rate on a scale of 1 to 4, with 4 being the highest score) - Quality rating of this SB 4321 - Quality rating of the Accomplishment Instructions 4321 - Quality rating of the Illustrations 4321 - Is this SB easy to understand ? Y/N If you have had difficulties in the accomplishment of this SB please quote below the area(s) and give a short description of the issue. Planning Material Instructions X Effectivity X Kit content X Preparation X Reason X List of Materials Operator Supplied X Mod/Inspection X Manpower X Industry support X Test X References X Re-identification X Close-Up X Publication X Tooling X Illustrations Comments:

Operator: Date: Name/Title: Please return this form to: AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE Attn : SEM4 Service Bulletins Management FAX : (33) 5 61 93 42 51 Or via your Resident Customer Support Office.

DATE: Feb 07/13 SERVICE BULLETIN No.: A340-55-5007 REVISION No.: 01 - Aug 20/14 Page: 1 6

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