# @A310 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 S IDE SHELL SANDWICH REPAIR INSPECTION MODIFICATION No.: None This page transmits Revision No.01 of Service Bulletin No.A310-55-2051 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 NOTE : Revision bars against references not identified in the CHANGES paragraph appear due to format changes introduced by new authorities’ rules. SUMMARY REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES REASON UPDATED R EFFECTIVITY OPERATOR LIST UPDATED R REFERENCES / REPERCUSSIONS REFERENCES/REPERCUSSIONS TABLE UPDATED R PLANNING INFORMATION EFFECTIVITY EFFECTIVITY RELATED INFORMATION UPDATED R Configuration definition CONF 001 CONFIGURATION DEFINITION UPDATED R REASON History HISTORY UPDATED R COMPLIANCE Accomplishment Timescale ACCOMPLISHMENT TIMESCALE UPDATED R DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 1 6

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

# @A310 SERVICE BULLETIN REVISION TRANSMITTAL SHEET 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 ACCOMPLISHMENT INSTRUCTIONS TASK 552051- 832-848-001-Inspection TASK SOLUTION UPDATED NOTE UPDATED R Subtask 552051-910-201-001 SUBTASK SOLUTION UPDATED QUANTITY UPDATED CONSUMABLE UPDATED MATERIAL LIST UPDATED REFERENCED DOCUMENTATION UPDATED R

Subtask 552051-941-201-001 SUBTASK SOLUTION UPDATED NOTE UPDATED R Subtask 552051-832-201-001 SUBTASK SOLUTION UPDATED FIGURE REFERENCE UPDATED NOTE UPDATED R Subtask 552051-832-202-001 SUBTASK SOLUTION UPDATED QUANTITY UPDATED CONSUMABLE UPDATED MATERIAL LIST UPDATED FIGURE REFERENCE UPDATED NOTE UPDATED R

Subtask 552051-832-203-001 SUBTASK SOLUTION UPDATED QUANTITY UPDATED CONSUMABLE UPDATED MATERIAL LIST UPDATED FIGURE REFERENCE UPDATED NOTE UPDATED R

Subtask 552051-832-204-001 SUBTASK SOLUTION UPDATED CONSUMABLE UPDATED FIGURE REFERENCE UPDATED NOTE UPDATED CONFIGURATION UPDATED MATERIAL LIST UPDATED R

Subtask 552051-832-205-001 SUBTASK SOLUTION UPDATED QUANTITY UPDATED CONSUMABLE UPDATED MATERIAL LIST UPDATED REFERENCED DOCUMENTATION UPDATED FIGURE REFERENCE UPDATED REFERENCES UPDATED R

DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 2 6

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

# @A310 SERVICE BULLETIN REVISION TRANSMITTAL SHEET Subtask 552051-832-206-001 SUBTASK SOLUTION UPDATED CONSUMABLE UPDATED FIGURE REFERENCE UPDATED NOTE UPDATED MATERIAL LIST UPDATED R

Subtask 552051-832-207-001 SUBTASK SOLUTION UPDATED QUANTITY UPDATED CONSUMABLE UPDATED MATERIAL LIST UPDATED REFERENCED DOCUMENTATION UPDATED NOTE UPDATED REFERENCES UPDATED R

Subtask 552051-833-201-001 SUBTASK SOLUTION UPDATED CONSUMABLE UPDATED QUANTITY UPDATED REFERENCED DOCUMENTATION UPDATED MATERIAL LIST UPDATED REFERENCES UPDATED R

Subtask 552051-832-208-001 SUBTASK SOLUTION ADDED N Subtask 552051-942-201-001 SUBTASK SOLUTION UPDATED R Fig. A-GBCAA Fig. A-GBCAA Sheet 02 SHEET 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 UPDATED R Fig. A-GBHAA Sheet 05 SHEET UPDATED R Fig. A-GBHAA Sheet 06 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
DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 3 6

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

# @A310 SERVICE BULLETIN REVISION TRANSMITTAL SHEET 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: Sep 11/12 REVISION No. : 01 - Aug 20/14

DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 4 6

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

# @A310 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 S IDE 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 A310 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: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 1 6

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

# @A310 SERVICE BULLETIN SUMMARY The accomplishment of this Service Bulletin will contribute to detect potential damage 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 ETOPS 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) :

18T 19U 40T 58X 82Z 85Z 98W 99Y AFG AIC BBC C9L CFC DGA F2I FDX GAF HFY IRA IRM IYE K1P KAC KZU MGL PCA PIA QAF R1T RJA ROT RZO SGX SUD THY TSC UBD UZB WHT 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 999.0070/10 OIT 999.0130/06 OIT 999.0067/12 AD 2014-0026 NATURE OF THE WORK AIRCRAFT YES EQUIPMENT NO HARD NO SOFT NO OBRM NO

DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 2 6

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

# @A310 SERVICE BULLETIN SUMMARY MANPOWER Task 552051-832-848-001: Inspection TOTAL MANHOURS 38.00 APPENDICES None

DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 3 6

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

# @A310 SERVICE BULLETIN SUMMARY
**CONF ALL

Z326 

### A

RUDDER SHELL TO BE INSPECTED 

### B



## A B LH SHOWN RH SHOWN B_SB_552051_6_SAAA_01_00 Figure A-G SAAA - S heet 01
DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 4 6

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

# @A310 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 S IDE 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 HF-1005 to HF-1323, HF-1325, HF-1327, HF-1329, HF-1331, HF-1332, HF-1340, TS-1324, TS-1326, TS-1328, TS-1330, TS-1333 to TS-1339, TS-1341 to TS-1420 or TS-2001 to TS-2197. NOTE : Repairs of rudder side shells which have been accomplished in accordance with a SRM procedure older than SRM December 2009 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 310-203 310-221 310-222 310-304 310-308 310-322 310-324 310-325 DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 1 6

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

# @A310 SERVICE BULLETIN (2) Effectivity by MSN 0162 0230 0237 0245 0248 0267 0278 0281 0283 0316 0331 0356 0362 0364 0369 0378 0394 0399 0407 0413 0418-0419 0421-0422 0425 0431 0434 0436-0437 0439 0441 0444-0447 0449 0452 0454 0456-0458 0467 0472-0473 0478 0480 0482-0484 0488-0492 0494-0500 0503 0519-0520 0522-0524 0526-0527 0537 0539 0545 0547 0549-0552 0562 0564-0565 0567-0568 0571 0574 0576 0585-0588 0590-0595 0597 0599-0600 0620 0622 0624 0636 0644 0646-0649 0651-0653 0656 0658 0660-0661 0663 0667 0671-0672 0674 0676 0678 0682 0687 0689 0691 0700 0702 0704 0706 (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 18T 0473 19U 0399 40T 0413 58X 0431 82Z 0550 0551 85Z 0527 98W 0495 99Y 0489 AFG 0496 0497 AIC 0407 BBC 0594 0700 C9L 0652 CFC 0425 0441 0444 0446 0482 DGA 0418 0421 0422 F2I 0520 FDX 0162 0230 0237 0245 0248 0267 0278 0281 0283 0316 0331 0356 0362 0364 0369 0378 0394 0439 0449 0452 0454 0456 0457 0458 0467 0492 0500 0539 0549 0552 0593 GAF 0434 0484 0498 0503 0522 0523 HFY 0565 IRA 0436 0671 IRM 0488 0499 0524 0537 0547 0564 0567 0586 0595 0620 IYE 0568 0702 0704 K1P 0648 KAC 0647 0649 0663 KZU 0592 0622 0646 MGL 0526 PCA 0419 PIA 0585 0587 0590 0653 0656 0660 0676 0678 0682 0687 0689 0691 QAF 0667 R1T 0591 DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 2 6

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

# @A310 SERVICE BULLETIN
OPERATOR MSN RJA 0445 0490 0491 ROT 0636 0644 RZO 0571 0624 0651 0661 SGX 0519 0562 SUD 0437 THY 0478 0480 TSC 0447 0472 0483 0545 0588 0597 0599 0600 0658 UBD 0672 0674 UZB 0574 0576 0706 WHT 0494 (4) Configuration by MSN MSN CONFIGURATION 0162 0230 0237 0245 0248 0267 0278 0281 0283 0316 0331 0356 0362 0364 0369 0378 0394 0399 0407 0413 0418 0419 0421 0422 0425 0431 0434 0436 0437 0439 0441 0444 0445 0446 0447 0449 0452 0454 0456 0457 0458 0467 0472 0473 0478 0480 0482 0483 0484 0488 0489 0490 0491 0492 0494 0495 0496 0497 0498 0499 0500 0503 0519 0520 0522 0523 0524 0526 0527 0537 0539 0545 0547 0549 0550 0551 0552 0562 0564 0565 0567 0568 0571 0574 0576 0585 0586 0587 0588 0590 0591 0592 0593 0594 0595 0597 0599 0600 0620 0622 0624 0636 0644 0646 0647 0648 0649 0651 0652 0653 0656 0658 0660 0661 0663 0667 0671 0672 0674 0676 0678 0682 0687 0689 0691 0700 0702 0704 0706 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

DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 3 6

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

# @A310 SERVICE BULLETIN 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. (2) Objective/Action This Service Bulletin details the inspection procedure to inspect affected rudders fitted on A310 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 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 552051-832-848-001: Inspection (1) Check the rudder repair records DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 4 6

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

# @A310 SERVICE BULLETIN (2) Identify the type, location and size of repairs on the rudder side shell CFRP areas in case of complete repair records since rudder 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 (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 Av iation Safety Agenc y (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 552051-832-201-001 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
DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 5 6

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

# @A310 SERVICE BULLETIN Table 1, Config. 001 - Rudder special detailed inspection for repair detection Condition Action Compliance time Repetitive interval Complete repair records since rudder 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

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 552051-832-203-001 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 552051-832-203-001 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 552051-832-205-001 Within 24 months from original Service Bulletin issue date None

DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 6 6

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

# @A310 SERVICE BULLETIN Table 2A, Config. 001 - Repair records are not complete or not available (CFRP 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 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 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 Subtask 552051-832-207-001 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 552051-832-207-001 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 552051-832-207-001 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 552051-832-205-001 Within 24 months from original Service Bulletin issue date None

DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 7 6

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

# @A310 SERVICE BULLETIN Table 2B, Config. 001 - Repair records are not complete or not available (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, 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 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 552051-832-202-001 Within 24 months from original Service Bulletin issue date None

Repair identified as a 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 552051-832-202-001 Within 24 months from original Service Bulletin issue date, before the pulse thermography inspection None

Repair identified as a type to be inspected Do a pulse thermography inspection on repair location in accordance with the accomplishment instructions Subtask 552051-832-202-001 or Identify the repair size by local sanding, refer to Subtask 552051-832-208-001 Within 24 months from original Service Bulletin issue date None

DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 8 6

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

# @A310 SERVICE BULLETIN Table 2C, Config. 001 - Repair records since rudder EIS are complete (CFRP areas) Condition Action Compliance time Repetitive interval 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 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 or local sanding Do an ELCH and/or UT inspection around the identified repairs in accordance with the accomplishment instructions Subtask 552051-832-205-001 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, 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 552051-832-207-001 Within 24 months from original Service Bulletin issue date, before the pulse thermography inspection None

DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 9 6

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

# @A310 SERVICE BULLETIN Table 2D, Config. 001 - Repair records since rudder EIS are complete (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 552051-832-207-001 or Identify the repair size by local sanding, refer to Subtask 552051-832-208-001 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 552051-832-207-001 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 552051-832-205-001 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, 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 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 552051-832-205-001 Before next flight None

DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 10 6

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

# @A310 SERVICE BULLETIN Table 3, Config. 001 - Fluid ingress detected Condition Action Compliance time Repetitive interval 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) (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 552051-832-204-001 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 500 FH or 4 months after closing holes At intervals not exceeding 500 FH or 4 months, whichever occurs later 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 552051-832-204-001 Within 1000 FC after closing holes Within intervals of 1000 Flight Cycles (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

DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 11 6

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

# @A310 SERVICE BULLETIN Table 3, Config. 001 - Fluid ingress detected Condition Action Compliance time Repetitive interval 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: 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.) 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.) 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

DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 12 6

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

# @A310 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 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 552051-832-206-001 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 500 FH or 4 months after closing the holes At intervals not exceeding 500 FH or 4 months, whichever occurs later 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

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 552051-832-205-001 Within 750 FC from first ELCH/UT inspection Every 750 FC from first ELCH/UT inspection

DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 13 6

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

# @A310 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 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 first 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 552051-832-206-001 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 500 FH or 4 months after closing the holes At intervals not exceeding 500 FH or 4 months, whichever occurs later 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

DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 14 6

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

# @A310 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 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.) =< 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 552051-832-206-001 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 500 FH or 4 months after closing the holes At intervals not exceeding 500 FH 4 months, whichever occurs later 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

DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 15 6

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

# @A310 SERVICE BULLETIN Table 5, Config. 001 - Hole closing in case of damaged outer skin during paint 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 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 552051-832-205-001 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
DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 16 6

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

# @A310 SERVICE BULLETIN Table 6.A, Config. 001 - Identify the repair size by local sanding 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 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 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 552051-832-205-001 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

DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 17 6

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

# @A310 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 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 552051-832-202-001 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

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 552051-832-205-001 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

DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 18 6

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

# @A310 SERVICE BULLETIN 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 552051-832-207-001 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 552051-832-207-001 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 552051-832-205-001 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 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.

DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 19 6

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

# @A310 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 552051-832-848-001: Inspection Get Access 1.00 On Aircraft Check the rudder repair records 4.00 Identify the type, location and size of repairs on the rudder side shell CFRP areas in case of complete repair records since rudder 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 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 DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 20 6

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

# @A310 SERVICE BULLETIN Steps Manhours Elapsed time Number of persons 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 20-16-00 24-00-00 55-40-00 55-42-11 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) 51-10-00 51-10-14 51-23-10 51-75-10 51-75-20 51-77-00 51-77-10 51-77-11 K. PUBLICATION AFFECTED None L. INTERCHANGEABILITY/MIXABILITY Not Applicable M. SPARES None

DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 21 6

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

# @A310 SERVICE BULLETIN

This Page Intentionally Left Blank

DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 22 6

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

# @A310 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: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 23 6

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

# @A310 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 TNO 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: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 24 6

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

# @A310 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: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 25 6

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

# @A310 SERVICE BULLETIN

This Page Intentionally Left Blank

DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 26 6

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

# @A310 SERVICE BULLETIN 3. ACCOMPLISHMENT INSTRUCTIONS Task 552051-832-848-001 - 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, A DHESIVES, 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: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 27 6

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

# @A310 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 552051-910-201-001 - Standard Practices Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-41-55, Page Block 001 20-16-00, Page Block 201 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 materials (Mat. No.) given in this Service Bulletin refer to Consumable Materials List (CML). (c) For circuit breaker safety practices, refer to AMM 20-16-00, Page Block 201. (d) The purpose of flow charts are for information only to show the various Inspection/Repair phases described in this Service Bulletin. (2) Subtask 552051-839-201-001 - 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 552051-941-201-001 - Job Set-up Manpower Resources Skills NON SPECIFIC

DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 28 6

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

# @A310 SERVICE BULLETIN
References Aircraft Maintenance Manual (AMM) 24-00-00, Page Block 301 55-40-00, Page Block 601 55-42-11, Page Block 401 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 24-00-00, Page Block 301. (b) In the cockpit, put warning notices in position to tell persons not to operate the flight controls. (c) Do the rudder inspection/check Job Set-up procedure, refer to AMM 55-40-00, Page Block 601, Para 1.B.(1)(a) thru (d). (d) Put a warning notice in the cockpit to tell persons not to pressurize the hydraulic systems. (e) Put access platforms in position at the rudder. (f) To remove the access panel 326AL from rudders which have not embodied Mod. 8827, refer to AMM 55-42-11, Page Block 401.

DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 29 6

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

# @A310 SERVICE BULLETIN C. PROCEDURE (1) Subtask 552051-832-201- 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 Sheet 02 Fig. A-GBCAA Repair type identification Sheet 01 - SRM list Sheet 02 - RAS list Fig. A-GBHAA Report sheet and sketches Sheet 01 - Pulse thermography report sheet Sheet 02 - Repair records report sheet Sheet 03 Sheet 04 Sheet 05 Sheet 06 Fig. A-GBJAA GFRP area location Sheet 01 Sheet 02 Sheet 03 (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 for rudder before Modification No. 8827, or as shown on Fig. A-GBAAA Sheet 02 for rudder after Modification No. 8827. 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 999.0070/10 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 December 2009, DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 30 6

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

# @A310 SERVICE BULLETIN - have been done in accordance with the SRM revision December 2009 or later, - have been accomplished in accordance with the SRM procedures as listed in Fig. A-GBCAA Sheet 01 , - are indicated in the AIRBUS Repair Approval Sheet (RAS) list Fig. AGBCAA Sheet 02 with "ISB inspection required: NO". NOTE : If you find a RAS which is not listed in the RAS list, contact AIRBUS and follow their instructions. 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 999.0070/10 and the situation did not change since then. 3 If repairs are recorded and the repair records are complete, refer to: - Subtask 552051-832-202-001 of this Service Bulletin for the rudder side shell areas made of CFRP. - Subtask 552051-832-207-001 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 have to be performed. For the identification of the GFRP areas, refer to the subsequent table: Rudder PN Refer to Figure A55471710 A55471730 Fig. A-GBJAA Sheet 02 A55471500 Fig. A-GBJAA Sheet 03 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 552051-832-203-001 of this Service Bulletin for the rudder side shell areas made of CFRP. - Subtask 552051-832-207-001 of this Service Bulletin for the upper rudder side shell areas made of GFRP.

DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 31 6

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

# @A310 SERVICE BULLETIN
6 If the repair records are not complete or not available, refer to: - Subtask 552051-832-203-001 of this Service Bulletin for the rudder side shell areas made of CFRP. - Subtask 552051-832-207-001 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 have to be performed. For the identification of the GFRP areas, refer to the subsequent table: Rudder PN Refer to Figure A55471710 A55471730 Fig. A-GBJAA Sheet 02 A55471500 Fig. A-GBJAA Sheet 03 (2) Subtask 552051-832-202-001 - Identify the type, location and size of repairs on the rudder side shell CFRP areas in case of comp lete repair records since rudder EIS are available 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 Textile-Lint Free Cotton 14SBA1 As required References Non Destructive Test Manual (NTM) 55-40-50 Page Block 1001 Structural Repair Manual (SRM) 51-75-10 51-75-20 Fig. A-GBBAA Repair type identification Sheet 01 Sheet 02 Fig. A-GBDAA Booster area definition Sheet 01 Sheet 02 Sheet 03 Sheet 04 DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 32 6

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

# @A310 SERVICE BULLETIN
References 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 inspection 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 Sheet 05 Sheet 06 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-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 999.0070/10 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 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 DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 33 6

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

# @A310 SERVICE BULLETIN 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 51-75-20 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 552051-833-201-001 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 55-40-50 Page Block 1001. NOTE : As an alternative for the pulse thermography inspection, you can identify the repair size by local sanding, refer to Subtask 552051-832-208-001. 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 552051-832-204-001 of this Service Bulletin.
DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 34 6

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

# @A310 SERVICE BULLETIN
7 Identify the booster areas in accordance with the subsequent table: Rudder PN Refer to Figure A55471710 A55471730 Fig. A-GBDAA Sheet 02 and Fig. A-GBDAA Sheet 03 A55471500 Fig. A-GBDAA Sheet 04 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 the subsequent table: Rudder PN Refer to Figure (sketch) A55471710 A55471730 Fig. A-GBHAA Sheet 03 and Fig. A-GBHAA Sheet 04 A55471500 Fig. A-GBHAA Sheet 05 and Fig. A-GBHAA Sheet 06 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 552051-832-205-001 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 552051-832-205-001 of this Service Bulletin. 11 After the inspection, restore the paint coating in accordance with the SRM 51-75-10. NOTE : Refer to OIT 999.0130/06 ’pai nt system - best practices’. (3) Subtask 552051-832-203-001 - 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 32.00 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: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 35 6

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

# @A310 SERVICE BULLETIN
References Non Destructive Test Manual (NTM) 55-40-50 , Page Block 1001 Structural Repair Manual (SRM) 51-75-10 51-75-20 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 Sheet 04 Fig. A-GBHAA Report sheet and sketches Sheet 01 - Pulse thermography report sheet Sheet 02 - Repair records report sheet Sheet 03 Sheet 04 Sheet 05 Sheet 06 Fig. A-GABAA Paint borer instructions Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 Sheet 08 (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 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. 13659. 2 Make sure that the paint thickness in the areas to be inspected 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. DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 36 6

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

# @A310 SERVICE BULLETIN

a If the paint coating and/or logo application is too thick, abrade the paint in acccordance with the SRM 51-75-20 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 552051-833-201-001 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 on the complete side shell CFRP areas (LH/RH) to identify repairs, refer to NTM 55-40-50 , Page Block 1001. 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 552051-832-204-001 of this Service Bulletin. 7 Identify the booster areas in accordance with the subsequent table: Rudder PN Refer to Figure A55471710 A55471730 Fig. A-GBDAA Sheet 02 and Fig. A-GBDAA Sheet 03
DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 37 6

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

# @A310 SERVICE BULLETIN
Rudder PN Refer to Figure A55471500 Fig. A-GBDAA Sheet 04 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 the subsequent table: Rudder PN Refer to Figure (sketch) A55471710 A55471730 Fig. A-GBHAA Sheet 03 and Fig. A-GBHAA Sheet 04 A55471500 Fig. A-GBHAA Sheet 05 and Fig. A-GBHAA Sheet 06 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 552051-832-205-001 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 552051-832-205-001 of this Service Bulletin. 11 After the inspection, restore the paint coating in accordance with the SRM 51-75-10. NOTE : Refer to OIT 999.0130/06 ’pai nt system - best practices’. (4) Subtask 552051-832-204-001 - 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 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 DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 38 6

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

# @A310 SERVICE BULLETIN
ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Trichloroethane Legacy 08BBU9 As required Laminating Resin-Epoxy Srm Type 2 13EBC1 As required
References Non Destructive Test Manual (NTM) 51-10-25 55-40-50 , Page Block 1001 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 Sheet 05 Sheet 06 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 552051-832-205-001 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 the subsequent table: Rudder PN Refer to Figure (sketch) A55471710 A55471730 Fig. A-GBHAA Sheet 03 and Fig. A-GBHAA Sheet 04 A55471500 Fig. A-GBHAA Sheet 05 and Fig. A-GBHAA Sheet 06 No further actions on these local single spots of fluid ingress in accordance with this Service Bulletin.

DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 39 6

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

# @A310 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 needed to close the drain holes: Pressure Sensitive Tape 05RFB1 As required

DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 40 6

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

# @A310 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 55-40-50 , Page Block 1001. 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 552051-832-205-001 - 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: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 41 6

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

# @A310 SERVICE BULLETIN
References Non Destructive Test Manual (NTM) 51-10-24, Page Block 401 51-10-26, Page Block 701 55-40-09 , Page Block 1001 Para 7 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 inspection 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 Sheet 05 Sheet 06 Fig. A-GBGAA Rudder skin thickness identification Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 (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 the subsequent table: Rudder PN Refer to Figure A55471710 A55471730 Fig. A-GBGAA Sheet 02 and Fig. A-GBGAA Sheet 03 A55471500 Fig. A-GBGAA Sheet 04 and Fig. A-GBGAA Sheet 05 (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, Page Block 701. 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, Page Block 701. b For the assessment criteria (yellow and red values) for the ELCH inspection, refer to NTM 55-40-09 , Page Block 1001 Para 7. DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 42 6

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

# @A310 SERVICE BULLETIN (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, Page Block 401. 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
. (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 the subsequent table: Rudder PN Refer to Figure (sketch) A55471710 A55471730 Fig. A-GBHAA Sheet 03 and Fig. A-GBHAA Sheet 04 A55471500 Fig. A-GBHAA Sheet 05 and Fig. A-GBHAA Sheet 06 (f) If no damage has been detected during the ELCH/UT inspection, continue with the steps given in the Subtask 552051-832-206-001 of this Service Bulletin. (6) Subtask 552051-832-206-001 - 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 DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 43 6

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

# @A310 SERVICE BULLETIN
References Fig. A-GBHAA Report sheet and sketches Sheet 01 - Pulse thermography report sheet Sheet 02 - Repair records report sheet Sheet 03 Sheet 04 Sheet 05 Sheet 06 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 (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 the subsequent table: Rudder PN Refer to Figure (sketch) A55471710 A55471730 Fig. A-GBHAA Sheet 03 and Fig. A-GBHAA Sheet 04 A55471500 Fig. A-GBHAA Sheet 05 and Fig. A-GBHAA Sheet 06 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 552051-832-205-001. 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 : Spots of fluid ingress behind the trailing edge screw line must not be vented.

DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 44 6

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

# @A310 SERVICE BULLETIN 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 needed 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. DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 45 6

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

# @A310 SERVICE BULLETIN
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 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 needed to close the drain holes: Pressure Sensitive Tape 05RFB1 As requiredLaminating ResinEpoxy Srm Type 2 13EBC1 As required Methyl-Ethyl-Ketone 08BBF1 As required DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 46 6

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

# @A310 SERVICE BULLETIN
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 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 DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 47 6

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

# @A310 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 needed 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: 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 552051-832-207- 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

DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 48 6

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

# @A310 SERVICE BULLETIN 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) 51-10-03, Page Block 501 51-10-19, Page Block 501 55-40-50 , Page Block 1001 Structural Repair Manual (SRM) 51-75-10 51-75-20 Fig. A-GBBAA Repair type identification Sheet 01 Sheet 02 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 inspection Sheet 05 - ELCH inspection grid 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-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 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. DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 49 6

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

# @A310 SERVICE BULLETIN

a If the paint coating and/or logo application is too thick, abrade the paint in accordance with the SRM 51-75-20 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 552051-833-201-001 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 55-40-50 , Page Block 1001. NOTE : As an alternative for the pulse thermography inspection, you can identify the repair size by local sanding, refer to Subtask 553043-832-208-001. 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 55-40-50 , Page Block 1001. 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 51-10-03, Page Block 501 or NTM 51-10-19, Page Block 501 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 552051-832-205-001 of this Service Bulletin. DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 50 6

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

# @A310 SERVICE BULLETIN
7 If fluid ingress has been detected, refer to Subtask 552051-832-204-001 of this Service Bulletin. 8 For further actions continue with the instructions given in the Subtask 552051-832-206-001 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 51-75-10. NOTE : Refer to OIT 999.0130/06 ’pai nt system - best practices’. (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 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 51-75-20 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 552051-833-201-001 for repair instructions. 2 Non Aqueous Cleaner-General 08BAA9 As required Textile-Lint Free Cotton 14SBA1 As required
DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 51 6

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

# @A310 SERVICE BULLETIN
3 Do a pulse thermography inspection on the complete GFRP area to identify repairs, refer to NTM 55-40-50 , Page Block 1001. 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 55-40-50 , Page Block 1001. 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 51-10-03, Page Block 501 or NTM 51-10-19, Page Block 501, 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 552051-832-205-001 of this Service Bulletin. 7 If fluid ingress has been detected, refer to Subtask 552051-832-204-001 of this Service Bulletin. 8 For further actions continue with the instructions given in the Subtask 552051-832-206-001 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 51-75-10. NOTE : Refer to OIT 999.0130/06 ’pai nt system - best practices’. (8) Subtask 552051-833-201-001 - 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 DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 52 6

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

# @A310 SERVICE BULLETIN
ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTESNon Aqueous CleanerGeneral 08BAA9 As required Laminating Resin-Epoxy Srm Type 2 13EBC1 As required Textile-Lint Free Cotton 14SBA1 As required References Structural Repair Manual (SRM) 51-75-10 51-77-00 Page Block 101 Para 6 51-77-10 Para 2 51-77-10 Para 3.D 51-77-11 Para 4.A.(3) 51-77-11 Para 4.E (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 51-77-10 Para 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.

DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 53 6

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

# @A310 SERVICE BULLETIN
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 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 and control the temperature by means of thermocouples in accordance with the SRM 51-77-10 Para 3.D. 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 51-77-00 Page Block 101 Para 6. 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 with: 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 51-75-10. (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.
DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 54 6

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

# @A310 SERVICE BULLETIN 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 51-77-10 Para 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

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 51-77-00 Page Block 101 Para 6. c Remove any surplus resin from the border area of the restoration. Use abrasive cloth. Start with 280 grade and finish with 400 grade.

DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 55 6

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

# @A310 SERVICE BULLETIN d Clean the restoration areas in accordance with the SRM 51-77-11 Para 4.E, with: 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 51-75-10. (9) Subtask 552051-832-208-001 - 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) 51-10-00 51-10-14 51-23-10 51-75-10 51-77-10 Para 2.D. 51-77-10 Para 2.E 51-77-10 Para 2.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 Sheet 04 Fig. A-GBHAA Report sheet and sketches Sheet 01
- Pulse thermography report sheet Sheet 02
- Repair records report sheet Sheet 03 Sheet 04 Sheet 05 Sheet 06

DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 56 6

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

# @A310 SERVICE BULLETIN
References 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 inspection 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. (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 51-77-10 Para 2.E. 3 Do a local mechanical sanding on top and around the repair in accordance with the SRM 51-77-10 Para 2.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 51-77-10 Para 2.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 51-10-00 thru SRM 51-10-14.
DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 57 6

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

# @A310 SERVICE BULLETIN

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 the subsequent table: Rudder PN Refer to Figure A55471710 A55471730 Fig. A-GBDAA Sheet 02 and Fig. A-GBDAA Sheet 03 A55471500 Fig. A-GBDAA Sheet 04 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 the subsequent table: Rudder PN Refer to Figure (sketch) A55471710 A55471730 Fig. A-GBHAA Sheet 03 and Fig. A-GBHAA Sheet 04 A55471500 Fig. A-GBHAA Sheet 05 and Fig. A-GBHAA Sheet 06 <1> Restore the surface protection in accordance with the SRM 51-75-10. 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 552051-832-205-001 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 552051-832-205-001 of this Service Bulletin. h If fluid ingress has been detected during the pulse thermography inspection, refer to Subtask 552051-832-204-001 of this Service Bulletin. i After the inspection, restore the paint coating in accordance with the SRM 51-75-10 and SRM 51-23-10. 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 51-77-10 Para 2.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 51-77-10 Para 2.G.. DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 58 6

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

# @A310 SERVICE BULLETIN 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 51-10-00 thru SRM 51-10-14. e Identify the booster areas in accordance with the subsequent table: Rudder PN Refer to Figure A55471710 A55471730 Fig. A-GBDAA Sheet 02 and Fig. A-GBDAA Sheet 03 A55471500 Fig. A-GBDAA Sheet 04 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 the subsequent table: Rudder PN Refer to Figure (sketch) A55471710 A55471730 Fig. A-GBHAA Sheet 03 and Fig. A-GBHAA Sheet 04 A55471500 Fig. A-GBHAA Sheet 05 and Fig. A-GBHAA Sheet 06 <1> Restore the surface protection in accordance with the SRM 51-75-10. 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 552051-832-205-001 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 552051-832-205-001 of this Service Bulletin. i If fluid ingress has been detected during the pulse thermography inspection, refer to Subtask 552051-832-204-001 of this Service Bulletin. j After the inspection, restore the paint coating in accordance with the SRM 51-75-10 and SRM 51-23-10. 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 51-77-10 Para 2.G.. DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 59 6

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

# @A310 SERVICE BULLETIN 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 552051-832-204-001 of this Service Bulletin. e Identify the booster areas in accordance with the subsequent table: Rudder PN Refer to Figure A55471710 A55471730 Fig. A-GBDAA Sheet 02 and Fig. A-GBDAA Sheet 03 A55471500 Fig. A-GBDAA Sheet 04 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 the subsequent table: Rudder PN Refer to Figure (sketch) A55471710 A55471730 Fig. A-GBHAA Sheet 03 and Fig. A-GBHAA Sheet 04 A55471500 Fig. A-GBHAA Sheet 05 and Fig. A-GBHAA Sheet 06 <1> Restore the surface protection in accordance with the SRM 51-75-10. 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 552051-832-205-001 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 552051-832-205-001 of this Service Bulletin.

DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 60 6

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

# @A310 SERVICE BULLETIN
i After the inspection, restore the paint coating in accordance with the SRM 51-75-10 and SRM 51-23-10. NOTE : Refer to OIT 999.0130/06 ’pai nt system - best practices’. D. TEST None E. CLOSE-UP (1) Subtask 552051-942-201-001 - Close-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 55-40-00, Page Block 601 55-42-11, Page Block 401 (a) Make sure that the work areas are clean and clear of tools and other items of equipment (b) To install the access panel 326AL on rudders, which have not embodied Mod. 8827, refer to AMM 55-42-11, Page Block 401. (c) Remove the access platforms. (d) Do the rudder inspection/check Close-up procedure, refer to AMM 55-40-00, Page Block 601. (e) In the cockpit, remove all warning notices.

DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 61 6

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

# @A310 SERVICE BULLETIN

**CONF ALL

NOTE: REMOVE AND INSTALL ACCESS PANEL AS PER AMM 55
− 42
− 11. POSITION OF RUDDER S/N PLACARD Z326



## A 326AL MFR DESCR. SER. N ° CA CODE MFG DATE A/C PNNSA9117−63D A55471XXXXXXX TS(HF)
− XXXX

01

01 

## B

B A C

VALID FOR RUDDERS BEFORE MODIFICATION NO.8827 B_SB_552051_6_BAAA_01_02 Figure A-G BAAA - S heet 01

Rudder SN identification DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 62 6

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

# @A310 SERVICE BULLETIN

**CONF ALL

POSITION OF RUDDER S/N PLACARD

VALID FOR RUDDERS AFTER MODIFICATION NO.8827 02

NOTE: USE A MIRROR OR FLEXIBLE ENDOSCOPE IF NECESSARY 02 

## C B 

## B MFR DESCR. SER. N ° CA CODE MFG DATE A/C PNNSA9117−63D A55471XXXXXXX TS(HF)
− XXXX

B_SB_552051_6_BAAA_02_00 Figure A-G BAAA - S heet 02

Rudder SN identification DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 63 6

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

# @A310 SERVICE BULLETIN

**CONF ALL

Z326 

### A

B_SB_552051_6_BBAA_01_00 

## A LH SHOWN RH SIMILAR



### A A B B
C C

D D E E F F

Figure A-G BBAA - S heet 01

Repair type identification DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 64 6

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

# @A310 SERVICE BULLETIN

**CONF ALL OUTER SKIN WITH AND WITHOUT CORE CLOSING

OUTER SKIN AND CORE REPAIR WITHOUT CORE CLOSING

OUTER SKIN AND CORE REPAIR WITH CORE CLOSING

BOTH SKIN AND CORE REPAIR

DELAMINATION AND CORE DAMAGE WITH CORE CLOSING (SRM 55
− 41
− 12 PAGE BLOCK 201 FIG.203) 

## A A

B B

C C (SRM 55
− 41
− 12 PAGE BLOCK 201 FIG.202)

(SRM 55
− 41
− 12 PAGE BLOCK 201 FIG.204/205)

(SRM 55
− 41
− 12 PAGE BLOCK 201 FIG.204/205)

(SRM 55
− 41
− 12 PAGE BLOCK 201 (SRM 55
− 41
− 12 PAGE BLOCK 201



## D D E E

F F FIG. 208A/208B/209 /211/212/213/213A/214/217) FIG. 208A/208B/209/211/212 /213/213A/214/217) BOTH SKIN AND CORE REPAIR WITH AND WITHOUT CORE CLOSING / REPAIR WITH ACCESS FROM BOTH SIDE WITH AND WITHOUT CORE CLOSING / REPAIR WITH ACCESS FROM ONE SIDE ONLY

B_SB_552051_6_BBAA_02_04 Figure A-G BBAA - S heet 02

Repair type identification DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 65 6

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

# @A310 SERVICE BULLETIN

**CONF ALL

REPAIR PROCEDURE PARA. FIG. CHAPTER A310 SRM ISSUE: 01. JUN 2009

12. 55
− 41
− 12 REPAIR OF LIGHTNING PROTECTION PLATE 207 13. 55
− 41
− 12 REPAIR OF APEX STRIP FOR STATIC DISCHARGER 208

20. 55
− 41
− 12 REPAIR OF LOWER SHELL EDGE 210 26. 55
− 41
− 12 REPLACEMENT OF BLINDNUT 215 27. 55
− 41
− 12 REPAIR OF DELAMINATION OF GFRP FITTING CONNECTION 1 THRU 7 216 29. 55
− 41
− 12 INSTALLATION OF REINFORCING PLATES FOR HANDHOLES 218

31. 55
− 41
− 12 REPAIR OF SKIN DAMAGE AT SCREW LINE 221, 222 AT GFRP FITTING CONNECTION 6 AND 7
(AROUND/NEAR SCREW POINTS) 32. 55
− 41
− 12 REPAIR OF DAMAGE AT LOWER AFT HOIST POINT 223 33. 55
− 41
− 12 REPAIR OF DAMAGE AT LOWER FWD HOIST POINT 224 34. 55
− 41
− 12 REPAIR OF DAMAGE AT UPPER HOIST POINT 225 30. 55
− 41
− 12 REPAIR OF SKIN DAMAGE IN REPAIR ZONE A AND ZONE J 219, 220 6. 55
− 41
− 12 REPAIR OF SURFACE CRACK 201 11. 55
− 41
− 12 REPAIR OF ATTACHMENT EDGE 206

16. 55
− 41
− 12 REPAIR OF APEX STRIP 208C 17. 55
− 41
− 12 TEMPORARY REPAIR FOR LARGE DAMAGE 208D 18. 55
− 41
− 12 208E TEMPORARY REPAIR FOR DEBONDING WITHOUT CRACKS AND HOLES

B_SB_552051_6_BCAA_01_03 Figure A-GBCAA - Sheet 01 Repair type identification - SRM list DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 66 6

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

# @A310 SERVICE BULLETIN

**CONF ALLFAMA/C TYPMSN AirlineRudder S/NDamagereport dateRAS ReferenceISB InspectionrequiredWBA300B4−600354PFDNOT REPORTED (HF−1078)17. OCT. 1994RAS/DAHAM/0216/94YESWBA310392AICHF−11373. DEC. 2007RAS/DAHAM/4023488/2007NOWBA310397FDXHF−109913. NOV.2008RAS/DAHAM/4026439/2008NOWBA310446CDNNOT REPORTED (NO DATA)29. MAR. 1995RAS/DAHAM/1028/95YESWBA310476THYNOT REPORTED (HF−1171)22. APR. 2002RAS/DAHAM/4015292/2002YESWBA310483TAPHF−119027. MAR. 2008RAS/DAHAM/4024646/2008NOWBA300B4−600530AIBHF−123623. JUN. 2005RAS/DAHAM/4019647/2005NOWBA300B4−600533GXYHF−12402. JAN. 2008RAS/DAHAM/4024029/2008NOWBA300B4−600536FDXHF−12448. NOV. 2007RAS/DAHAM/4023298/2007NOWBA310537THYNOT REPORTED (HF−1255)10. JUN. 2002RAS/DAHAM/4015486/2002YESWBA300B4−600540MONHF−12424. MAR. 2008RAS/DAHAM/4024490/2008NOWBA310541TAPHF−126021. DEC. 2007RAS/DAHAM/4024000/2007NOWBA300B4−600558TARNOT REPORTED (HF−1261)12. JAN. 2004RAS/DAHAM/4017787/2004YESWBA310565TAPNOT REPORTED (HF−1289)23. OCT. 2006RAS/DAHAM/4021406/2006YESWBA300B4−600604MONHF−127020. FEB. 2008RAS/DAHAM/4024422/2008NOWBA300B4−600624AUATS−134328. JAN.1998RAS/DAHAM/1019/98YESWBA300B4−600630FDXTS−135121. JUN. 1999RAS/DAHAM/4025917/2008NOWBA300B4−600713CESNOT REPORTED (TS−1418)21. OCT. 2003RAS/DAHAM/4011302/1999YESWBA300B4−600782THANOT REPORTED (TS−2080)31. JUL. 2002RAS/DAHAM/4017547/2003YESWBA300B4−600824UPSNOT REPORTED (TS−2123)RAS/DAHAM/4015671/2002YESWBA300F4−600858AHKTS−21508. AUG. 2006RAS/DAHAM/4021168/2006YESWBWB ALLSPAREUPSTS−219429. DEC. 2008RAS/DAHAM/4026846/2008NO19. SEP. 2008WB434HF−1136RAS/DAHAM/4023199/2007NOWBHF−1163RAS/DAHAM/4025922/2008NOA310A310447GAFTSC17.OCT.200718.SEP.2008

B_SB_552051_6_BCAA_02_03 Figure A-GBCAA - Sheet 02 Repair type identification - RAS list DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 67 6

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

# @A310 SERVICE BULLETIN

**CONF ALL

Z326



## A A

B D

B_SB_552051_6_BDAA_01_00 

### C D

Figure A-GBDAA - Sheet 01 Booster area definition DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 68 6

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

# @A310 SERVICE BULLETIN

**CONF ALL

DEFINITION OF BOOSTER AREA VALID FOR RUDDER A55471730 A55471710 

## B LH SHOWN 1040.0 mm (40.94 in) 1760.0 mm (69.30 in) 2070.0 mm (81.50 in)

BR1 BR2 BR3

BR4 BR5 BR6 BR7

B_SB_552051_6_BDAA_02_00 Figure A-GBDAA - Sheet 02 Booster area definition DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 69 6

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

# @A310 SERVICE BULLETIN

**CONF ALL

DEFINITION OF BOOSTER AREA

VALID FOR RUDDER A55471730 A55471710 1035.0 mm (40.75 in) 2000.0 mm (78.74 in) 1950.0 mm (76.77 in)

BR1 BR2 BR3 BR4 BR5 BR6 BR7



## C RH SHOWN

B_SB_552051_6_BDAA_03_00 Figure A-GBDAA - Sheet 03 Booster area definition DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 70 6

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

# @A310 SERVICE BULLETIN

**CONF ALL

DEFINITION OF BOOSTER AREA VALID FOR RUDDER A55471500 LH SHOWN RH SYMMETRICAL

675.0 mm (26.57 in) 1060.0 mm (41.73 in) 2950.0 mm (116.14 in)

BR1 BR3 BR4 BR5 BR6 BR7

BR2

B_SB_552051_6_BDAA_04_00 

## D

Figure A-GBDAA - Sheet 04 Booster area definition DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 71 6

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

# @A310 SERVICE BULLETIN

**CONF ALL

Z326



## A A

B E

B E

B_SB_552051_6_BEAA_01_01 Figure A-G BEAA - S heet 01 Typical pulse thermography and ELCH/UT inspection DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 72 6

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

# @A310 SERVICE BULLETIN

**CONF ALL

TYPICAL PULSE THERMOGRAPHY INSPECTION LH SHOWN RH SYMETRICAL BR1 BR2 BR3

BR4 BR5 BR6 BR7



## B C

D

B_SB_552051_6_BEAA_02_02 Figure A-G BEAA - S heet 02 Typical pulse thermography and ELCH/UT inspection - Repair size assessment DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 73 6

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

# @A310 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

B_SB_552051_6_BEAA_03_02 Figure A-G BEAA - S heet 03 Typical pulse thermography and ELCH/UT inspection - Repair size assessment DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 74 6

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

# @A310 SERVICE BULLETIN

**CONF ALL

TYPICAL ELCH/UT INSPECTION LH SHOWN RH SYMETRICAL BR1 BR2 BR3

BR4 BR5 BR6 BR7

MAX. REPAIR PLY

INSPECTION AREA ELCH/UT A 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 F

B_SB_552051_6_BEAA_04_01 Figure A-G BEAA - S heet 04 Typical pulse thermography and ELCH/UT inspection - Boundary and grid of ELCH/UT inspection DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 75 6

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

# @A310 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 B_SB_552051_6_BEAA_05_06 Figure A-G BEAA - S heet 05 Typical pulse thermography and ELCH/UT inspection - ELCH inspection grid DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 76 6

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

# @A310 SERVICE BULLETIN

**CONF ALL

Z326



## A A

B B

B_SB_552051_6_BFAA_01_00 Figure A-GBFAA - Sheet 01 Core ventilation procedure DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 77 6

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

# @A310 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 MAX. REPAIR PLY 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 INSPECTION THROUGH THE DRILL HOLE.) 

## 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

B_SB_552051_6_BFAA_02_05 Figure A-GBFAA - Sheet 02 Core ventilation procedure DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 78 6

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

# @A310 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. B_SB_552051_6_BFAA_03_01 Figure A-GBFAA - Sheet 03 Core ventilation procedure DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 79 6

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

# @A310 SERVICE BULLETIN

**CONF ALL

Z326



## A A

C E

B D

B_SB_552051_6_BGAA_01_00 Figure A-GBGAA - Sheet 01 Rudder skin thickness identification DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 80 6

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

# @A310 SERVICE BULLETIN

**CONF ALL

< 1.5mm (0.059 in) VALID FOR RUDDER A55471730 LH SHOWN BR1 BR2 BR3

BR4 BR5 BR6 BR7

SKIN THICKNESS A55471710 > 1.5mm (0.059 in) SKIN THICKNESS NO INSPECTION 

## B

B_SB_552051_6_BGAA_02_00 Figure A-GBGAA - Sheet 02 Rudder skin thickness identification DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 81 6

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

# @A310 SERVICE BULLETIN

**CONF ALL

< 1.5mm (0.059 in) VALID FOR RUDDER A55471730 RH SHOWN SKIN THICKNESS

A55471710 > 1.5mm (0.059 in) SKIN THICKNESS NO INSPECTION BR1 BR2 BR3 BR4 BR5 BR6 BR7



## C

B_SB_552051_6_BGAA_03_00

Figure A-GBGAA - Sheet 03 Rudder skin thickness identification DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 82 6

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

# @A310 SERVICE BULLETIN

**CONF ALL

< 1.5mm (0.059 in) VALID FOR RUDDER A55471500 LH SHOWN BR1 BR2 BR3

BR4 BR5 BR6 BR7

33 38

10

SKIN THICKNESS LIGHTNING PROTECTION PLATE

LIGHTNING PROTECTION PLATE

LIGHTNING PROTECTION PLATE
NO INSPECTION 

## D

B_SB_552051_6_BGAA_04_00 Figure A-GBGAA - Sheet 04 Rudder skin thickness identification DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 83 6

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

# @A310 SERVICE BULLETIN

**CONF ALL

VALID FOR RUDDER A55471500 RH SHOWN BR1 BR2 BR3 BR4

BR5 BR6 BR7

30 40

10 LIGHTNING PROTECTION PLATE

LIGHTNING PROTECTION PLATE

LIGHTNING PROTECTION PLATE < 1.5mm (0.059 in) SKIN THICKNESS NO INSPECTION 

## E

B_SB_552051_6_BGAA_05_00 Figure A-GBGAA - Sheet 05 Rudder skin thickness identification DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 84 6

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

# @A310 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
− 2051 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

B_SB_552051_6_BHAA_01_05 Figure A-GBHAA - Sheet 01 Report sheet and sketches - Pulse thermography report sheet DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 85 6

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

# @A310 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
− 2051 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.: A310
− 55
− 2051 REVXX IN CASE OF MORE THAN 1 REPAIR, DUPLICATE THIS REPORTING SHEET (0 FLIGHT CYCLES) EIS ENTRY INTO SERVICE AUTHORITIES (NO AIRBUS APPROVAL)

B_SB_552051_6_BHAA_02_03 Figure A-GBHAA - Sheet 02 Report sheet and sketches - Repair records report sheet DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 86 6

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

# @A310 SERVICE BULLETIN

**CONF ALL 

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

## Sandwich Repair Inspection

LH

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

## A55471730 A55471710

BR1 BR2 BR3

BR4 BR5 BR6 BR7

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

B_SB_552051_6_BHAA_03_01 Figure A-GBHAA - Sheet 03 Report sheet and sketches DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 87 6

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

# @A310 SERVICE BULLETIN

**CONF ALL 

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

## Sandwich Repair Inspection

RH

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

## A55471730 A55471710

NOTE: FOR THE DAMAGE LOCATION, MARK THE AREA AND IDENTIFY WITH A NUMBER. 01 01 BR1 BR2 BR3 BR4 BR5 BR6 BR7

B_SB_552051_6_BHAA_04_01 Figure A-GBHAA - Sheet 04 Report sheet and sketches DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 88 6

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

# @A310 SERVICE BULLETIN

**CONF ALL 

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

## Sandwich Repair Inspection

LH

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

## A55471500

BR1 BR2 BR3

BR4 BR5 BR6 BR7

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

LIGHTNING PROTECTION PLATE

B_SB_552051_6_BHAA_05_01 Figure A-GBHAA - Sheet 05 Report sheet and sketches DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 89 6

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

# @A310 SERVICE BULLETIN

**CONF ALL 

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

## Sandwich Repair Inspection

RH

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

## A55471500

NOTE: FOR THE DAMAGE LOCATION, MARK THE AREA AND IDENTIFY WITH A NUMBER. 01 01 BR1 BR2 BR3 BR4 BR5 BR6 BR7

LIGHTNING PROTECTION PLATE

LIGHTNING PROTECTION PLATE

B_SB_552051_6_BHAA_06_00

Figure A-GBHAA - Sheet 06 Report sheet and sketches DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 90 6

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

# @A310 SERVICE BULLETIN

**CONF ALL

Z326



## A

B_SB_552051_6_BJAA_01_00 

### B C B C A

Figure A-GBJAA - Sheet 01 GFRP area location DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 91 6

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

# @A310 SERVICE BULLETIN

**CONF ALL

VALID FOR RUDDER 

## B LH SHOWN 378.0 mm (14.88 in)

BR1 BR2 BR3

BR4 BR5 BR6 BR7

RH SYMMETRICAL 924.0 mm (36.38 in) GFRP AREA

CFRP AREA

A55471730 A55471710
B_SB_552051_6_BJAA_02_00 Figure A-GBJAA - Sheet 02 GFRP area location DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 92 6

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

# @A310 SERVICE BULLETIN

**CONF ALL

VALID FOR RUDDER A55471500 LH SHOWN RH SYMMETRICAL BR1 BR3 BR4 BR5 BR6

BR2 512.0 mm (20.16 in) BR7 985.0 mm (38.78 in) GFRP AREA

CFRP AREA

B_SB_552051_6_BJAA_03_00 

## C

Figure A-GBJAA - Sheet 03 GFRP area location DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 93 6

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

# @A310 SERVICE BULLETIN

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

NO YES

PERFORM PULSE THERMOGRAPHY INSPECTION ON COMPLETE FLUID REPAIR TYPE INSPECTED IN ACCORDANCE WITH THE SB. 02 IDENTIFIED TO BE REPORT THE INFORMATION TO AIRBUS. 01

PERFORMED SINCE RUDDER EIS ?

REPAIR DETECTED, WHICH

NO

YES REPAIR

YES NO
REPORT THE INFORMATION TO AIRBUS.

PERFORM PULSE THERMOGRAPHY ON REPAIR LOCATION TO PRECISE LOCATION AND SIZE.

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. YES NO COMPLETE REPAIR RECORDS AVAILABLE SINCE RUDDER EIS ?

YES NO NO FURTHER ACTIONS. CONTINUE WITH ACTIONS AS PER FLOW CHART 3.

REPAIRS.

NO YES

REPORT THE INFORMATION TO AIRBUS. SIDE SHELLS TO IDENTIFY REPAIRS: MARK THE 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 REPAIRS IN THE BOOSTER AREA REPAIR SIZE 55000mm2 LARGER THAN 03 (85.25 sq.in.) 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

12 FOR PAINT THICKNESS IDENTIFICATION REFER TO FLOW CHART 5

FOR PAINT THICKNESS IDENTIFICATION REFER TO FLOW CHART 5 INGRESS DETECTED

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

NOTE: REFER TO FIGURE A
− GFAAA, SHEET 06. 26 LOCAL PAINT THICKNESS IDENTIFICATION 27

MARK REPAIR SIZE ON SURFACE 22 23 25

B_SB_552051_6_FAAA_01_06 Figure A-GFAAA - Sheet 01

Flow Chart - Flow Chart 1 DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 94 6

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

# @A310 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. 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. THEIR INSTRUCTIONS REPAIR TO AIRBUS SBO 5, COPY SEES2 REPAIR TO AIRBUS SBO 5, COPY SEES2

19 19
NOTE: REFER TO FIGURE A
− GFAAA, SHEET 06. B_SB_552051_6_FAAA_02_06 Figure A-GFAAA - Sheet 02

Flow Chart - Flow Chart 2 DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 95 6

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

# @A310 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

B_SB_552051_6_FAAA_03_07 Figure A-GFAAA - Sheet 03

Flow Chart - Flow Chart 3 DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 96 6

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

# @A310 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 18 WHICH ARE NOT MANUFACTURING REWORKS 20 20 21

NOTE: REFER TO FIGURE A
− GFAAA, SHEET 06. B_SB_552051_6_FAAA_04_04 Figure A-GFAAA - Sheet 04

Flow Chart - Flow Chart 4 DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 97 6

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

# @A310 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 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

NOTE: REFER TO FIGURE A
− GFAAA, SHEET 06. B_SB_552051_6_FAAA_05_04 Figure A-GFAAA - Sheet 05

Flow Chart - Flow Chart 5 DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 98 6

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

# @A310 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 999.0070/10 CONTINUE WITH THE REPAIR SIZE DEFINED BY THE LARGEST REPAIR PLY. 06 ONLY MANUFACTURING HOT
− CURING REWORKS ARE DOCUMENTED IN AOT 55A2048 AND ISB 55
− 2049. 07 MANUFACTURING REWORK COMPLETE DATA. AIRBUS MUST BE CONTACTED FOR 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
− 20 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
− 10 PARA 2.C. PERFORM A LOCAL MECHANICAL SANDING A STEP BY STEP BASIS UP TO INITIAL BASIC PRIMER LAYER. AS PER SRM 51
− 77
− 10 PARA 2.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
− 10 PARA 2.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!

B_SB_552051_6_FAAA_06_01 Figure A-GFAAA - Sheet 06 Flow Chart DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 99 6

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

# @A310 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 500 FH or 4 months, 1. Apply high speed tape over the ventilation hole, refer to Chapter 51
− 77
− 11 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
− 10 Paragraph 2.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
− 00, Paragraph 3.D 4. Prepare the laminating resin (Material No. 13EBC1), refer to Chapter 51
− 77
− 10, Paragraph 2.A 5. Prepare the repair plies (MIL
− C
− 9084C TYPE VIIIA or B
−style 7781 dry glass fabric), refer to Chapter 51
− 77
− 10, Paragraph 2.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
− 10, Paragraph 2.A 7. Apply repair plies to the repair area as shown in Figure 1, refer to Chapter 51
− 77
− 10, Paragraph 2.H 8. If the repair cure shall be accelerated by heat:

−Install the vaccum bag, refer to Chapter 51
− 77
− 10, Paragraph 3.D, respect modificatons shown on Figure 2 and the heating equipment.

−Allow repair to cure under vacuum pressure, refer to Chapter 51
− 77
− 10, Paragraph 3.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
− 10, Paragraph 3.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
− 10, Paragraph 3.D. and respect modifications shown on Figure 2.

−Allow repair to cure under vacuum pressure, refer to Chapter 51
− 77
− 10, Paragraph 3.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
− 00, Paragraph 6. 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 08BBU1), refer to Chapter 51
− 77
− 10, Paragraph 2.E. 13. Restore the surface protection, refer to Chapter 51
− 75
− 10. whichever occurs later.

B_SB_552051_6_AAAA_01_04 Figure A-G AAAA - S heet 01 Closing of ventilation holes DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 100 6

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

# @A310 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
− 10, PARAGRAPH 3.D. 

## Figure 2
−Bagging for curing process
B_SB_552051_6_AAAA_02_01 Figure A-G AAAA - S heet 02 Closing of ventilation holes DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 101 6

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

# @A310 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 TNO PAINT BORER. DESCRIPTION 1. GENERAL A. THIS PROCEDURE CONTAINS THE INSPECTION PROCEDURE DESCRIBING PAINT THICKNESS MEASUREMENT USING THE TNO 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 TNO PAINT BORER. C. JOB SETUP INFORMATION

(1) TOOLING LIST INSPECTION: PAINT THICKNESS MEASUREMENT TNO PAINT TOOL: BORER KIT MODEL 518 OR 518S OR 518MC WITH DIFFERENT DRILLS PREFERABLY THE FOLLOWING: DRILL DRILL MEASURING RANGE CUTTING ANGLE 26.6° 45° FACTOR ( m/sc.div) 10 20 ADDITIONAL DOCUMENT: OPERATING MANUAL TNO PAINT BORER NOTE: FOR THIS INSPECTION ALSO OLDER OR NEWER VERSIONS OF THE TNO PAINT BORER MIGHT BE USED. IT IS IMPORTANT TO HAVE THE ABOVE 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. SPECIFIED DRILLS AVAILABLE. ( m) 10
− 1000 20
− 2000

B_SB_552051_6_ABAA_01_04 Figure A-G ABAA - S heet 01 Paint borer instructions DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 102 6

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

# @A310 SERVICE BULLETIN

**CONF ALL

2 PROCEDURE:
1. PREPARE THE TNO 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 TNO PAINT BORER 518 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

B_SB_552051_6_ABAA_02_04 Figure A-G ABAA - S heet 02 Paint borer instructions DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 103 6

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

# @A310 SERVICE BULLETIN

**CONF ALL

Z326



## A A

LH SHOWN RH SIMILAR CFRP AREA GFRP AREA 

### C D E

B D E

B_SB_552051_6_ABAA_03_00 Figure A-G ABAA - S heet 03 Paint borer instructions DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 104 6

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

# @A310 SERVICE BULLETIN

**CONF ALL
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 D E F

G

B_SB_552051_6_ABAA_04_01 Figure A-G ABAA - S heet 04 Paint borer instructions DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 105 6

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

# @A310 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)

B_SB_552051_6_ABAA_05_00 Figure A-G ABAA - S heet 05 Paint borer instructions DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 106 6

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

# @A310 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

B_SB_552051_6_ABAA_06_00 Figure A-G ABAA - S heet 06 Paint borer instructions DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 107 6

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

# @A310 SERVICE BULLETIN

**CONF ALL

B_SB_552051_6_ABAA_07_00 Figure A-G ABAA - S heet 07 Paint borer instructions DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 108 6

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

# @A310 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

200.00mm (7.87in.) FROM BR2 RIVET 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.)

B_SB_552051_6_ABAA_08_02 Figure A-G ABAA - S heet 08 Paint borer instructions DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 109 6

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

# @A310 SERVICE BULLETIN REPORTING SHEET 

### TITLE: STABILIZERS - RUDDER S IDE 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 concer ned (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: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 1 6

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

# @A310 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: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051 REVISION No.: 01 - Aug 20/14 Page: 1 6

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