# @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. 

# MANDATORYMANDATORYMANDATORY
ATA SYSTEM: 55 

### TITLE: STABILIZERS - RUDDER - A310 RUDDER DEBOND INSPECTION **CONF ALL MODIFICATIONS None REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES On AIRBUS A310 aircraft, most of the rudder side shells are sandwich structures made of Carbon Fiber Reinforced Plastic (CFRP) and Glass Fiber Reinforced Plastic (GFRP) with a honeycomb core, like on AIRBUS Single Aisle family aircraft. A debonding in a rudder shell was found on the rudder of an A319 and an A321 aircraft. A large rudder debond, resulting from an undetected damage growth, could affectthe handling quality of the aircraft. Under specific conditions, a large debond could lead to aircraft inflight instability. A review of the production records revealed that the debonding reported on both rudders correspond to areas that had been reworked in production. This Service Bulletin details the special detailed inspection procedure to inspect the reworked areas on affected rudders fitted on A310 aircraft for potential debonding. Due to the different areas on the rudder to be inspected, different inspection procedures are necessary: - Vacuum loss inspection - Elasticity Laminate Checker (ELCH) inspection - Tap test inspection - Thermography inspection - Ultrasound (US) inspection. The accomplishment of this Service Bulletin will ensure the detection of potential debonding in the reworked areas.

DATE: Mar 16/10 SERVICE BULLETIN No.: A310-55-2049 REVISION No.: 00 - Mar 16/10 Page: 1 6

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# @A310 SERVICE BULLETIN SUMMARY GENERAL EVALUATION EVALUATION TABLE COMPLIANCE MANDATORY CANCELS INSPECTION SB NO POTENTIAL AD YES A/C OPERATION AFFECTED NO RELIABILITY AFFECTED NO PAX COMFORT AFFECTED NO COST SAVING NO ETOPS AFFECTED NO STRUCTURAL LIFE EXTN NO VENDOR SB INVOLVED NO MATERIAL PRICE INFORMATION No Material EFFECTIVITY This Service Bulletin is applicable to this (these) operator(s) :

19U 52X 58X 82Z 85Z 99Y A1L AFG AIB AIC BAF BBC BLE CFC CSA DAH DEC DGA F2I FDX GAF HFY I2L IRA IRM IYE JAB JAV KAC KTC KYV KZU MGL MWA PIA QAF R1T RJA ROT RZO SBI SGX SUD THY TSC UZB WHT CONCURRENT REQUIREMENTS None REFERENCES / REPERCUSSIONS TFU 55.40.12.001 OEB None AOT 55A2048 SIL None LINE MAINTENANCE AFFECTED No LIFE LIMIT None OTHER SBIT 914.0808/09 NATURE OF THE WORK AIRCRAFT YES EQUIPMENT NO HARD NO SOFT NO OBRM NO MANPOWER Task 552049-832-848-001: Inspection TOTAL MANHOURS 2.00 APPENDICES None
DATE: Mar 16/10 SERVICE BULLETIN No.: A310-55-2049 REVISION No.: 00 - Mar 16/10 Page: 2 6

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# @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



# MANDATORYMANDATORYMANDATORY
ATA SYSTEM: 55 

### TITLE: STABILIZERS - RUDDER - A310 RUDDER DEBOND 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 (1) Models 310-203 310-203C 310-204 310-221 310-222 310-304 310-308 310-322 310-324 310-325 (2) Effectivity by MSN 0162 0191 0201 0217 0224 0230 0233 0237 0241 0245 0248 0251 0254 0257 0264 0267 0273 0278 0281 0283 0288 0291 0293 0297 0303 0309 0316 0318 0320 0326 0331 0333 0335 0338-0339 0342-0343 0345-0346 0349 0353 0356-0357 0359-0360 0362 0364 0367 0370 0372 0375 0378-0379 0386 0389-0390 0392 0394 0397 0399-0400 0406-0407 0410 0413 0416 0418 0421-0422 0425 0427-0429 0431 0434 0436-0437 0439 0441 0444-0449 0452 0454 0456-0458 0467 0472-0473 0475-0476 0478 0480-0492 0494-0499 0502-0503 0519-0520 0522-0524 0526-0527 0531 0534 0537-0539 0541-0542 0544-0545 0547 0549-0552 0562 0564-0565 0567-0568 0571 0573-0574 0576 0585-0588 0590-0595 0597 0599-0600 0620 0622 0624 0636 0638 0640 0642 0644 0646-0654 0656 0658 0660-0661 0663 0665 0667 0669 0671-0672 0674 0676 0678 0680 0682 0684 0686-0687 0689 0697 0706

DATE: Mar 16/10 SERVICE BULLETIN No.: A310-55-2049 REVISION No.: 00 - Mar 16/10 Page: 1 6

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# @A310 SERVICE BULLETIN (3) Effectivity by Operator The Operator/MSN relationship is provided for information only and is correct at the time of issue in accordance with the information available to AIRBUS. Any future changes resulting from transfer of an aircraft from one operator to another will not be reflected in this list unless the Service Bulletin is revised for another reason. OPERATOR MSN 19U 0399 52X 0410 58X 0431 82Z 0550 0551 85Z 0595 99Y 0489 A1L 0648 AFG 0496 0497 AIB 0686 AIC 0392 0406 0407 0413 0428 0429 0538 0544 0654 0665 0669 0680 BAF 0367 0372 BBC 0594 BLE 0650 CFC 0425 0441 0444 0446 0482 CSA 0672 0674 DAH 0291 0293 DEC 0684 0697 DGA 0418 0421 0422 F2I 0309 FDX 0162 0191 0201 0217 0224 0230 0233 0237 0241 0245 0248 0251 0254 0257 0264 0267 0273 0278 0281 0283 0288 0297 0303 0316 0318 0326 0331 0333 0335 0339 0342 0343 0345 0346 0349 0353 0356 0359 0360 0362 0364 0378 0394 0397 0400 0439 0449 0452 0454 0456 0457 0458 0467 0492 0534 0539 0542 0549 0552 0593 0638 GAF 0434 0484 0498 0499 0503 0522 0523 HFY 0495 0565 I2L 0640 0642 IRA 0338 0370 0375 0379 0389 0390 0436 0671 IRM 0488 0537 0564 0586 IYE 0568 JAB 0320 JAV 0357 0481 KAC 0647 0649 0663 KTC 0524 0567 0620 KYV 0386 KZU 0592 0622 0646 MGL 0526 MWA 0652 PIA 0473 0585 0587 0590 0653 0656 0660 0676 0678 0682 0687 0689
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# @A310 SERVICE BULLETIN

OPERATOR MSN QAF 0667 R1T 0591 RJA 0416 0445 0490 0491 0531 ROT 0636 0644 RZO 0571 0624 0651 0661 SBI 0427 0475 0486 0487 0520 SGX 0519 0562 SUD 0437 THY 0476 0478 0480 0502 TSC 0447 0472 0483 0485 0527 0541 0545 0547 0588 0597 0599 0600 0658 UZB 0574 0576 0706 WHT 0448 0494 0573 (4) Configuration by MSN MSN CONFIGURATION 0162 0191 0201 0217 0224 0230 0233 0237 0241 0245 0248 0251 0254 0257 0264 0267 0273 0278 0281 0283 0288 0291 0293 0297 0303 0309 0316 0318 0320 0326 0331 0333 0335 0338 0339 0342 0343 0345 0346 0349 0353 0356 0357 0359 0360 0362 0364 0367 0370 0372 0375 0378 0379 0386 0389 0390 0392 0394 0397 0399 0400 0406 0407 0410 0413 0416 0418 0421 0422 0425 0427 0428 0429 0431 0434 0436 0437 0439 0441 0444 0445 0446 0447 0448 0449 0452 0454 0456 0457 0458 0467 0472 0473 0475 0476 0478 0480 0481 0482 0483 0484 0485 0486 0487 0488 0489 0490 0491 0492 0494 0495 0496 0497 0498 0499 0502 0503 0519 0520 0522 0523 0524 0526 0527 0531 0534 0537 0538 0539 0541 0542 0544 0545 0547 0549 0550 0551 0552 0562 0564 0565 0567 0568 0571 0573 0574 0576 0585 0586 0587 0588 0590 0591 0592 0593 0594 0595 0597 0599 0600 0620 0622 0624 0636 0638 0640 0642 0644 0646 0647 0648 0649 0650 0651 0652 0653 0654 0656 0658 0660 0661 0663 0665 0667 0669 0671 0672 0674 0676 0678 0680 0682 0684 0686 0687 0689 0697 0706 001

(5) Configuration definition **CONF 001 is valid for aircraft with rudders which might have reworked areas to be inspected. (6) Material Effectivity MATERIAL QTY PER A/C SEE NOTES Consumable CMLD01 1 B. CONCURRENT REQUIREMENTS None

DATE: Mar 16/10 SERVICE BULLETIN No.: A310-55-2049 REVISION No.: 00 - Mar 16/10 Page: 3 6

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# @A310 SERVICE BULLETIN
C. REASON (1) History On AIRBUS A310 aircraft, most of the rudder side shells are sandwich structures made of Carbon Fiber Reinforced Plastic (CFRP) and Glass Fiber Reinforced Plastic (GFRP) with a honeycomb core, like on AIRBUS Single Aisle family aircraft. A debonding in a rudder shell was found on the rudder of an A319 and an A321 aircraft. A large rudder debond, resulting from an undetected damage growth, could affect the handling quality of the aircraft. Under specific conditions, a large debond could lead to aircraft in-flight instability. A review of the production records revealed that the debonding reported on both rudders correspond to areas that had been reworked in production. (2) Objective/Action This Service Bulletin details the special detailed inspection procedure to inspect the reworked areas on affected rudders fitted on A310 aircraft for potential debonding. Due to the different areas on the rudder to be inspected, different inspection procedures are necessary: - Vacuum loss inspection - Elasticity Laminate Checker (ELCH) inspection - Tap test inspection - Thermography inspection - Ultrasound (US) inspection. (3) Advantages The accomplishment of this Service Bulletin will ensure the detection of potential debonding in the reworked areas. (4) Operational/Maintenance Consequences None D. DESCRIPTION To accomplish this Service Bulletin it is necessary to : Task 552049-832-848-001: Inspection (1) Do the rudder special detailed inspection on aircraft with rudders which will not exceed 13000 FC within 24 month after the issue of this Service Bulletin (2) Do the rudder special detailed inspection on aircraft with rudders which have exceeded or will exceed 13000 FC within 24 month after the issue of this Service Bulletin

DATE: Mar 16/10 SERVICE BULLETIN No.: A310-55-2049 REVISION No.: 00 - Mar 16/10 Page: 4 6

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# @A310 SERVICE BULLETIN
E. COMPLIANCE (1) Classification MANDATORY (2) Accomplishment Timescale Table 1. Config. 001 - Rudder special detailed inspection on aircraft with rudders which will not exceed 13000 FC within 24 month after the issue of this Service Bulletin. Area to be inspected Condition Action Compliance time Repetitive interval N/A N/A Identify the Serial Number of the installed rudder Within 24 month after the issue of this SB N/A
Area 1 N/A Vacuum loss inspection in accordance with Subtask 552049-832-201 -002 Within 24 month after the issue of this SB N/A

Area 1 Damage indications found during the vacuum loss inspection Report to AIRBUS Before next flight N/A

Area 1 No damage indications found during the vacuum loss inspection Report to AIRBUS Within 10 days after the vacuum loss inspection N/A

Area 1 No damage indications found during the vacuum loss inspection Temporary option 1: Close the vacuum loss inspection holes with adhesive tape Before next flight, if the temporary option 2 or the permanent restoration have not been accomplished N/A

Area 1 No damage indications found during the vacuum loss inspection Temporary option 1: Do a detailed inspection of the restored area for loose or lost adhesive tape N/A At intervals not exceeding 4 months

Area 1 Loose or lost tape found Temporary option 1: Close the vacuum loss inspection holes again with adhesive tape Before next flight, if the temporary option 2 or the permanent restoration have not been accomplished N/A

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# @A310 SERVICE BULLETIN

Area to be inspected Condition Action Compliance time Repetitive interval Area 1 No damage indications found during the vacuum loss inspection Temporary option 1: Do the permanent restoration. Do a thermography or ultrasound inspection before the resin injection Within 4500 FC after the vacuum loss inspection N/A

Area 1 No damage indications found during the vacuum loss inspection Temporary option 2: Close the vacuum loss inspection holes with resin and adhesive tape. Do a thermography or ultrasound inspection before the resin injection Before next flight, if the temporary option 1 or the permanent restoration have not been accomplished N/A

Area 1 Damage indications found during the thermography or ultrasound inspection Temporary option 2: Report to AIRBUS Before next flight N/A

Area 1 No damage indications found during the thermography or ultrasound inspection Temporary option 2: Restore the surface protection Within 4500 FC after the vacuum loss inspection N/A

Area 1 No damage indications found Permanent restoration: Do a thermography or ultrasound inspection before the resin injection Before next flight after the vacuum loss inspection or within 4500 FC after the vacuum loss inspection if the temporary option 1 or the temporary option 2 has been accomplished N/A

Area 1 Damage indications found during thermography or ultrasound inspection Permanent restoration: Report to AIRBUS Before next flight N/A

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# @A310 SERVICE BULLETIN

Area to be inspected Condition Action Compliance time Repetitive interval Area 1 No damage indications found during thermography or ultrasound inspection No further action after accomplishment of the permanent restoration N/A N/A

Area 2 N/A ELCH inspection in accordance with Subtask 552049-832-201 -002 within 24 month after the issue of this SB N/A

Area 2 Damage indications found during ELCH inspection Re-examine the damage indications as per tap test inspection and report to AIRBUS Before next flight N/A

Area 2 No damage indications found during the ELCH inspection Report to AIRBUS and do 2 additional repetitive ELCH inspections Report within 10 days after the 1. ELCH inspection Within intervals between 4000 and 4500 FC Area 2 Damage indications found during the 1. or 2. additional repetitive ELCH inspection Re-examine the damage indications as per tap test inspection and report to AIRBUS Before next flight N/A

Area 2 No damage indications found during the 2 additional repetitive ELCH inspections Report to AIRBUS No further action Report within 10 days after the ELCH inspections N/A

Table 2. Config. 001 - Rudder special detailed inspection on aircraft with rudders which have already exceeded 13000 FC or will exceed 13000 FC within 24 month after the issue of this Service Bulletin. Area to be inspected Condition Action Compliance time Repetitive interval N/A N/A Identify the Serial Number of the installed rudder within 8 month after the issue of this SB N/A
Area 1 N/A Vacuum loss inspection in accordance with Subtask 552049-832-202 -002 within 8 month after the issue of this SB N/A

DATE: Mar 16/10 SERVICE BULLETIN No.: A310-55-2049 REVISION No.: 00 - Mar 16/10 Page: 7 6

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# @A310 SERVICE BULLETIN

Area to be inspected Condition Action Compliance time Repetitive interval Area 1 Damage indications found during the vacuum loss inspection Report to AIRBUS Before next flight N/A

Area 1 No damage indications found during the vacuum loss inspection Temporary option 1: Close the vacuum loss inspection holes with adhesive tape Before next flight, if the temporary option 2 or the permanent restoration have not been accomplished N/A

Area 1 No damage indications found during the vacuum loss inspection Temporary option 1: Do a detailed inspection of the restored area for loose or lost adhesive tape N/A At intervals not exceeding 4 months

Area 1 Loose or lost tape found Temporary option 1: Close the vacuum loss inspection holes again with adhesive tape Before next flight, if the temporary option 2 or the permanent restoration have not been accomplished N/A

Area 1 No damage indications found during the vacuum loss inspection Temporary option 1: Do the permanent restoration. Do a thermography or ultrasound inspection before the resin injection Within 4500 FC after the vacuum loss inspection N/A

Area 1 No damage indications found during the vacuum loss inspection Temporary option 2: Close the vacuum loss inspection holes with resin and adhesive tape. Do a thermography or ultrasound inspection before the resin injection Before next flight, if the temporary option 1 or the permanent restoration have not been accomplished N/A

Area 1 Damage indications found during thermography or ultrasound inspection Temporary option 2: Report to AIRBUS Before next flight N/A

DATE: Mar 16/10 SERVICE BULLETIN No.: A310-55-2049 REVISION No.: 00 - Mar 16/10 Page: 8 6

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# @A310 SERVICE BULLETIN

Area to be inspected Condition Action Compliance time Repetitive interval Area 1 No damage indications found during thermography or ultrasound inspection Temporary option 2: Restore the surface protection Within 4500 FC after the vacuum loss inspection N/A

Area 1 No damage indications found during the vacuum loss inspection Permanent restoration: Do a thermography inspection before the resin injection Before next flight after the vacuum loss inspection or within 4500 FC after the vacuum loss inspection if the temporary option 1 or the temporary option 2 has been accomplished N/A

Area 1 Damage indications found during thermography or ultrasound inspection Permanent restoration: Report to AIRBUS Before next flight N/A

Area 1 No damage indications found during thermography or ultrasound inspection No further action after accomplishment of the permanent restoration N/A N/A

Area 2 N/A ELCH inspection in accordance with Subtask 552049-832-202 -002 within 24 month after the issue of this SB N/A

Area 2 Damage indications found during ELCH inspection Re-examine the damage indications as per tap test inspection and report to AIRBUS Before next flight N/A

Area 2 No damage indications found during ELCH inspection Report to AIRBUS and do 2 additional repetitive ELCH inspections Report within 10 days after the 1. ELCH inspection ELCH inspection within intervals between 4000 and 4500 FC Area 2 Damage indications found during the 1. or 2. additional repetitive ELCH inspection Re-examine the damage indications as per tap test inspection and report to AIRBUS Before next flight N/A

DATE: Mar 16/10 SERVICE BULLETIN No.: A310-55-2049 REVISION No.: 00 - Mar 16/10 Page: 9 6

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# @A310 SERVICE BULLETIN

Area to be inspected Condition Action Compliance time Repetitive interval Area 2 No damage indications found during the 2 additional repetitive ELCH inspections Report to AIRBUS No further action Within 10 days after the ELCH inspection N/A

Accomplishment of this Service Bulletin is expected to be rendered mandatory by the issue of an Airworthiness Directive (AD) published by the European Aviation Safety Agency (EASA). It is anticipated that the AD will confirm the (thresholds and/or intervals and/or date) given above but reference should be made to the AD for confirmation of the mandated accomplishment timescale. F. APPROVAL Approved under EASA Design Organization Approval No. EASA21J.031. If an aircraft listed in the effectivity has a modification or repair embodied that is not of AIRBUS origin, and which affects the content of this Service Bulletin, the operator is responsible for obtaining approval by its airworthiness authority for any adaptation necessary before incorporation of the Service Bulletin. 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 552049-832-848-001: Inspection Get Access 1.00 On Aircraft Do the rudder special detailed inspection on aircraft with rudders which will not exceed 13000 FC within 24 month after the issue of this Service Bulletin 0 Do the rudder special detailed inspection on aircraft with rudders which have exceeded or will exceed 13000 FC within 24 month after the issue of this Service Bulletin 0
Close-Up 1.00 TOTAL MANHOURS 2.00 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 (39.37 in.) for the different inspection procedures: Steps Manhours Elapsed time Number of persons
DATE: Mar 16/10 SERVICE BULLETIN No.: A310-55-2049 REVISION No.: 00 - Mar 16/10 Page: 10 6

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# @A310 SERVICE BULLETIN

Get access 1.00 0.75 2 Rudder SN identification 0.25 0.25 1 Vacuum inspection 2.00 1.50 2 Thermography inspection 0.25 0.25 2 Ultrasound inspection 0.25 0.25 1 ELCH inspection 0.75 0.75 1 Tap inspection 0.25 0.25 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 24-00-00 29-10-00 55-33-13 55-40-00 Consumable Material List (CML) Non Destructive Test Manual (NTM) 51-10-03 51-10-19 51-10-24 51-10-25 51-10-26 51-10-28 Structural Repair Manual (SRM) 51-75-12 51-77-10 51-77-11 K. PUBLICATION AFFECTED None L. INTERCHANGEABILITY/MIXABILITY Not Applicable M. SPARES None

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# @A310 SERVICE BULLETIN

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# @A310 SERVICE BULLETIN
2. MATERIAL INFORMATION **CONF ALL A. MATERIAL - PRICE AND AVAILABILITY (1) Procurement Addresses This Service Bulletin is the subject of an AIRBUS monitored retrofit campaign. (2) Price and Availability None B. INDUSTRY SUPPORT INFORMATION AIRBUS will credit the manhours indicated in this Service Bulletin for inspections that are performed on aircraft in warranty at the time of such inspection. Credit will be at the operator’s agreed in-house warranty labor rate. Claims for labor allowance should be received not later than 90 days after completion of the last affected warranted aircraft. This Service Bulletin is subject of specific support provided by AIRBUS. For details please contact your Customer Support Director. For the organisation of this retrofit, operators are kindly requested to contact AIRBUS retrofit management department. AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX France Tel : (33) 5 67 19 06 22 E-mail : monitored.retrofit@airbus.com Fax : (33) 5 61 93 27 45 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 Self-Adhes. Disks 05-052 As required Self Adhesive Aluminium Tape 08-052 As required Solvent General Purpose 11-026 As required Lint-Free Cotton Cloth 19-003 As required Wet Lay Up Resin 20-022 As required (2) Components None

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# @A310 SERVICE BULLETIN (3) Equipment None E. PARTS TO BE RE-IDENTIFIED BY OPERATOR None F. TOOLING (1) Tooling - Price and Availability None (2) Tools To find the correct tool-PN for the different inspection tools, refer to the subsequent table: Inspection tool PN NTM reference ELCH Elasticity Laminate Checker Kit MBBBT100 51-10-26 Vacuum loss Vacuum cup TL3AMB1420T28L 51-10-28 Thermography Thermography kits 99A55407320000 (Camera and monitor) and 99A55407321000 (complementary tooling including hot air blower) 51-10-25

Ultrasound US-equipment EPOCH4PLUS and search unit K1SM and reference block MBBGCFRPHC200 and cable PKLL2 51-10-24

tap test tap test inspection test tool 98A57103013000 or 99A55209001000 51-10-03
tap test Function test block and Woodpecker 99A55407291000 and WP632 or WP632AM 51-10-19

For more detailed information, refer to the related NTM chapter. (3) Special Tools None

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# @A310 SERVICE BULLETIN
3. ACCOMPLISHMENT INSTRUCTIONS Task 552049-832-848-001 - Inspection WARNING: MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND THE CAUTIONS INCLUDED IN THE REFERENCED PROCEDURES. WARNING: PUT THE SAFETY DEVICES AND THE WARNING NOTICES IN POSITION BEFORE YOU START A TASK ON OR NEAR : - THE FLIGHT CONTROLS - THE FLIGHT CONTROL SURFACES - THE LANDING GEAR AND THE RELATED DOORS - COMPONENTS THAT MOVE. WARNING: MAKE SURE THAT THE FLIGHT CONTROL SAFETY-LOCKS AND THE WARNING NOTICES ARE IN POSITION. CAUTION: DO NOT CAUSE DAMAGE TO THE SURFACES. THE COMPONENTS ARE MADE OF CARBONFIBER REINFORCED PLASTIC. Task Associated Data Manpower TOTAL MANHOURS 2.00 A. GENERAL (1) Subtask 552049-910-201-001 - Standard Practices Manpower Resources Skills NON SPECIFIC Material necessary to do the job Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Solvent General Purpose 11-026 As required Lint-Free Cotton Cloth 19-003 As required References Aircraft Maintenance Manual (AMM) 06-41-55, Page Block 001 Consumable Material List (CML) (a) For location of the access panels, (Refer to AMM 06-41-55, Page Block 001). (b) For the specification of consumable materials (Mat. No.) that you must use in this Service Bulletin, (Refer to Consumable Material List (CML)). DATE: Mar 16/10 SERVICE BULLETIN No.: A310-55-2049 REVISION No.: 00 - Mar 16/10 Page: 15 6

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# @A310 SERVICE BULLETIN (c) Clean the areas to be inspected with Solvent General Purpose 11-026 As required
and Lint-Free Cotton Cloth 19-003 As required (2) Subtask 552049-839-201-001 - Documentation Manpower Resources Skills NON SPECIFIC (a) Write in the applicable aircraft records that you have done all the work given in this Service Bulletin. B. PREPARATION (1) Subtask 552049-941-201-001 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 24-00-00, Page Block 301 29-10-00, Page Block 301 55-33-13, Page Block 401 55-40-00, Page Block 601 (a) Make sure that the aircraft is electrically grounded (Refer to AMM 24-00-00, Page Block 301). (b) Check the documentation of the related aircraft for further repairs on the rudder during service. If you find documents about further repairs, contact AIRBUS. (c) In the cockpit, put warning notices in position to tell persons not to operate the flight controls. (d) Do the rudder inspection/check Job Set-up procedure (Refer to AMM 55-40-00, Page Block 601 pata (a) to (d)). (e) Put a warning notice in the cockpit to tell persons not to pressurize the hydraulic systems. (f) Put access platform(s) in position at the rudder. (g) To open the access panels, (Refer to AMM 55-33-13, Page Block 401).

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# @A310 SERVICE BULLETIN
C. PROCEDURE (1) Subtask 552049-832-201-002 - Do the rudder special detailed inspection on aircraft with rudders which will not exceed 13000 FC within 24 month after the issue of this Service Bulletin Manpower Resources Manhours 0 Minimum number of person 0 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 NOTES Self-Adhes. Disks 05-052 As required Self Adhesive Aluminium Tape 08-052 As required Solvent General Purpose 11-026 As required Wet Lay Up Resin 20-022 As required References Non Destructive Test Manual (NTM) 51-10-03, Page Block 701 51-10-19, Page Block 701 51-10-24, Page Block 401 51-10-25, Page Block 101 Procedure A and B 51-10-26, Page Block 701 51-10-28, Page Block 701 Structural Repair Manual (SRM) 51-75-12 51-77-10 51-77-11 Para 4.M.(2) 51-77-11 Para 4.A.(3) 51-77-11 Para 5. 51-77-11 Para 4.E

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# @A310 SERVICE BULLETIN

References Fig. A-GAAAA Rudder inspection Sheet 01 - Flow Chart 1, vacuum loss inspection area 1 Sheet 02 - Vacuum loss inspection - damage assessment Sheet 03 - Flow Chart 2, ELCH inspection area 2 Sheet 05 - Reporting sheet Sheet 06 - Rudder SN identification Sheet 07 - Inspection areas Sheet 08 - Typical ELCH procedure Sheet 09 - Rudder skin thickness LH Sheet 10 - Rudder skin thickness RH Sheet 11 - Rudder skin thickness LH Sheet 12 - Rudder skin thickness RH Fig. A-GACAA rudder SN - MSN reference list Sheet 01 (a) Identify the Serial Number (SN) of the rudder as shown on Fig. A-GAAAA Sheet 06

. (b) If you do not find a SN placard on the rudder, contact AIRBUS for further instructions. (c) Compare the rudder SN with the rudder SNs in the rudder SN - MSN reference list Fig. A-GACAA Sheet 01

. 1 If you find a different SN against the MSN as detailed in the rudder SN - MSN reference list, contact AIRBUS for further instructions. 2 If the rudder SN is not part of the rudder SN - MSN reference list, refer to the Close-up para 3.E. No further action is necessary. 3 If the rudder SN is part of the rudder SN - MSN reference list with the same indicated MSN, continue with the below instructions. (d) The Technical Disposition (TD) details the location of the reworked area to be inspected and includes information about the vacuum loss vacuum loss inspection holes, if necessary. 1 For the definition of the areas to be inspected refer to the rudder SN - MSN reference list Fig. A-GACAA Sheet 01 to find the MSN related Technical Disposition (TD) No. 2 To get the TD, refer to the SB BOOKLET-link on the index page of this Service Bulletin on the Air@Nav Engineering page in AIRBUS WORLD and use ’SB BOOKLET-TD-K45-S1-XXXXX’. For additional information, refer to SBIT SEMB 914.0808/09

DATE: Mar 16/10 SERVICE BULLETIN No.: A310-55-2049 REVISION No.: 00 - Mar 16/10 Page: 18 6

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# @A310 SERVICE BULLETIN

3 Inspection method for reworked areas: - For reworked area astride AREA 1 and AREA 2, if TD provides vacuum loss hole location then rework must be treated as if in AREA 1 only. - For reworked area astride AREA 1 and AREA 2, if TD does not provide vacuum loss hole location then rework must be treated as if in AREA 2 only. (e) If there are only areas on the trailing edge, shown as ’area 2’ on the Fig. A-GAAAA Sheet 07, to be inspected, refer to Para (g). (f) If there is another area, shown as ’area 1’ on the Fig. A-GAAAA Sheet 07, to be inspected, do the subsequent inspection in accordance with the Flow Chart Fig. AGAAAA Sheet 01 and Fig. A-GAAAA Sheet 02: 1 Do the vacuum loss inspection within 24 month after the issue of this Service Bulletin (Refer to NTM 51-10-28, Page Block 701).
a Temporarily install adhesive tape on the areas to be inspected. b Mark the grid of holes on the adhesive tape.
c CAUTION: DRILL PENETRATION INTO THE SANDWICH STRUCTURE HAS TO BE LIMITED TO 20 mm (0.8 in.) TO PREVENT INNER SKIN DAMAGE. Drill the vacuum loss inspection holes with DIA 1.5 mm (0.06 in.) through the outer skin only. d Do the Vacuum loss inspection (Refer to NTM 51-10-28, Page Block 701).
e In case of damage indications, report to AIRBUS on the basis of a detailed referenced damage report for further instructions before next flight. f In case of no damage indications, close the vacuum loss inspection holes as detailed in the subsequent instructions and report the result to AIRBUS within 10 days. 2 Temporary restoration of the vacuum loss inspection holes option 1:
a Close the holes with Self Adhesive Aluminium Tape 08-052 As required

or Self-Adhes. Disks 05-052 As required

DATE: Mar 16/10 SERVICE BULLETIN No.: A310-55-2049 REVISION No.: 00 - Mar 16/10 Page: 19 6

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# @A310 SERVICE BULLETIN
b Do a detailed inspection of the restored area at intervals not exceeding 4 month. Inspect the restored area for loose or lost adhesive disks or tape.
c In case of loose or lost tape ordisks, close the holes again with Self Adhesive Aluminium Tape 08-052 As required

or Self-Adhes. Disks 05-052 As required d This temporary restoration must be replaced by the permanent restoration within 4500 FC after the vacuum loss inspection. 3 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. Temporary restoration of the vacuum loss inspection holes option 2:
a Before the resin injection: <1> Identify the skin thickness of the areas to be inspected, refer to the subsequent table: Rudder SN Refer to Figure HF-1122, HF-1254 TS-1362 Fig. A-GAAAA Sheet 09 and Fig. A-GAAAA Sheet 10 TS-2006, TS-2008,. TS-2010 TS-2027, TS-2030, TS-2033 TS-2043, TS-2048, TS-2049 TS-2054, TS-2055 TS-2059 TS-2061 TS-2071 thru TS-2073 TS-2082 TS-2084 thru TS-2087 Fig. A-GAAAA Sheet 11 and Fig. A-GAAAA Sheet 12

<2> If the skin thickness of the affected areas, defined by the TD, does not exceed 1.5 mm (0.06 in.), do a thermography inspection as detailed in NTM 51-10-25, Page Block 101 Procedure A and B AND/OR

DATE: Mar 16/10 SERVICE BULLETIN No.: A310-55-2049 REVISION No.: 00 - Mar 16/10 Page: 20 6

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# @A310 SERVICE BULLETIN If the skin of the affected areas, defined by the TD, is thicker than 1.5 mm (0.06 in.), do an ultrasound inspection as detailed in NTM 51-10-24, Page Block 401. NOTE: During the ultrasound inspection, the vacuum loss inspection holes must be closed with thin adhesive tape (Material No 08-052 - basic) to prevent couplant ingress into the holes. b In case of damage indications contact AIRBUS for further instructions before next flight.
c Prepare and dry the restoration area (Refer to SRM 51-77-11 Para 4.M.(2)). d Prepare Wet Lay Up Resin 20-022 As required (Refer to SRM 51-77-11 Para 4.A.(3)). 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.
e Warm up the mixed resin to a maximum temperature of 45 ̊C (113 F). f 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 vacuum loss inspection hole. g Close the filled holes with Self Adhesive Aluminium Tape 08-052 As required

or Self-Adhes. Disks 05-052 As required h 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 in accordance with the resin manufacturer recommendations and perform a gelation test outside the restoration area. After resin gelation plus 2h, the aircraft can be released to operations again. i Within 4500 FC after the vacuum loss inspection, do the final surface restoration: <1> Remove the self adhesive tape from the restoration areas.

DATE: Mar 16/10 SERVICE BULLETIN No.: A310-55-2049 REVISION No.: 00 - Mar 16/10 Page: 21 6

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# @A310 SERVICE BULLETIN <2> Inspect the restoration (Refer to SRM 51-77-11 Para 5.). <3> Remove any surplus resin from the border area of the restoration. Use abrasive cloth. Start with 280 grade and finish with 400 grade. <4> Clean the restoration areas with Solvent General Purpose 11-026 As required (Refer to SRM 51-77-11 Para 4.E). <5> Restore the surface protection (Refer to SRM 51-75-12). 4 Permanent restoration of the vacuum loss inspection holes:
a Before the resin injection: <1> Identify the skin thickness of the areas to be inspected, refer to the subsequent table: Rudder SN Refer to Figure HF-1122, HF-1254 TS-1362 Fig. A-GAAAA Sheet 09 and Fig. A-GAAAA Sheet 10 TS-2006, TS-2008,. TS-2010 TS-2027, TS-2030, TS-2033 TS-2043, TS-2048, TS-2049 TS-2054, TS-2055 TS-2059 TS-2061 TS-2071 thru TS-2073 TS-2082 TS-2084 thru TS-2087 Fig. A-GAAAA Sheet 11 and Fig. A-GAAAA Sheet 12

<2> If the skin thickness of the affected areas, defined by the TD, does not exceed 1.5 mm (0.06 in.), do a thermography inspection as detailed in NTM 51-10-25, Page Block 101 Procedure A and B AND/OR If the skin of the affected areas, defined by the TD, is thicker than 1.5 mm (0.06 in.), do an ultrasound inspection as detailed in NTM 51-10-24, Page Block 401. NOTE: During the ultrasound inspection, the vacuum loss inspection holes must be closed with thin adhesive tape (Material No 08-052 - basic) to prevent couplant ingress into the holes. b In case of damage indications contact AIRBUS for further instructions before next flight.
c DATE: Mar 16/10 SERVICE BULLETIN No.: A310-55-2049 REVISION No.: 00 - Mar 16/10 Page: 22 6

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# @A310 SERVICE BULLETIN
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 (Refer to SRM 51-77-11 Para 4.M.(2)). d Prepare Wet Lay Up Resin 20-022 As required (Refer to SRM 51-77-11 Para 4.A.(3)). 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.
e Warm up the mixed resin to a maximum temperature of 45 ̊C (113 F). f 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 vacuum loss inspection hole. g Close the filled holes with a self adhesive tape. h 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 in accordance with the resin manufacturer recommendations and perform a gelation test outside the restoration area. After resin gelation plus 4 h, continue with the subsequent steps: <1> Remove the self adhesive tape from the restoration areas. <2> Inspect the restoration (Refer to SRM 51-77-11 Para 5.). <3> Remove any surplus resin from the border area of the restoration. Use abrasive cloth. Start with 280 grade and finish with 400 grade. <4> Clean the restoration areas with Solvent General Purpose 11-026 As required (Refer to SRM 51-77-11 Para 4.E).
DATE: Mar 16/10 SERVICE BULLETIN No.: A310-55-2049 REVISION No.: 00 - Mar 16/10 Page: 23 6

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# @A310 SERVICE BULLETIN <5> Restore the surface protection (Refer to SRM 51-75-12). (g) If there are areas on the trailing edge, shown as ’area 2’ on the Fig. A-GAAAA Sheet 07, to be inspected, do a special detailed inspection (ELCH) in accordance with the Flow Chart Fig. A-GAAAA Sheet 03: 1 Do the ELCH inspection within 24 month after the issue of this Service Bulletin (Refer to NTM 51-10-26, Page Block 701).
a For the ELCH inspection behind the fasteners, use one grid line with a distance of 50 mm (1.97 in.) between the inspection points, as shown on Fig. A-GAAAA Sheet 08, View D and View E, area 2. <1> The assessment criteria for the ELCH inspection behind the fasteners are: Yellow value 0.30 mm (0.012 in.) Red value 0.40 mm (0.016 in.) For the adjustment of the ELCH, refer to NTM 51-10-26, Page Block 701. b If the ELCH inspection extends ahead of the fasteners, use an inspection grid of 50 mm X 50 mm (1.97 in.) between the inspection points, as shown on Fig. A-GAAAA Sheet 08, View D and View E, area 1. <1> The assessment criteria for the ELCH inspection ahead of the fasteners are: Yellow value 0.25 mm (0.010 in.) Red value 0.35 mm (0.014 in.) For the adjustment of the ELCH, refer to NTM 51-10-26, Page Block 701. 2 In case of damage indications, re- examine the findings as per tap test inspection (Refer to NTM 51-10-03, Page Block 701 or NTM 51-10-19, Page Block 701), contact AIRBUS for further instructions before next flight. 3 In case of no damage indications, report to AIRBUS within 10 days and do 2 additional ELCH inspections at intervals not exceeding 4500 FC and not less than 4000 FC.
a In case of damage indications during the additional ELCH inspection, reexamine the findings as per tap test inspection (Refer to NTM 51-10-03, Page Block 701 or NTM 51-10-19, Page Block 701), and contact AIRBUS for further instructions before next flight. b In case of no damage indications during the additional ELCH inspections, report to AIRBUS within 10 days.

DATE: Mar 16/10 SERVICE BULLETIN No.: A310-55-2049 REVISION No.: 00 - Mar 16/10 Page: 24 6

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# @A310 SERVICE BULLETIN (h) Fill in the reporting sheet, refer to Fig. A-GAAAA Sheet 05

. In case of damage indications, send the inspection report with a referenced mail to: AIRTAC Customer Services AIRBUS Central Entity 1 ROND POINT MAURICE BELLONTE 31707 BLAGNAC CEDEX FRANCE Phone: +33(0)5 61 93 3400 (24 hour) Fax: +33(0)5 61 93 3500 Mailto: airtac@airbus.com and in case of damage indications or no damage indications to Structure Engineering Support Customer Services - SEES1 AIRBUS Central Entity 1 ROND POINT MAURICE BELLONTE 31707 BLAGNAC CEDEX FRANCE Fax: +33(0)5 61 93 36 14 (2) Subtask 552049-832-202-002 - Do the rudder special detailed inspection on aircraft with rudders which have exceeded or will exceed 13000 FC within 24 month after the issue of this Service Bulletin Manpower Resources Manhours 0 Minimum number of person 0 Subtask elapsed time 0 Skills NON DESTRUCTIVE TESTING

DATE: Mar 16/10 SERVICE BULLETIN No.: A310-55-2049 REVISION No.: 00 - Mar 16/10 Page: 25 6

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# @A310 SERVICE BULLETIN
Material necessary to do the job Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Self-Adhes. Disks 05-052 As required Self Adhesive Aluminium Tape 08-052 As required Solvent General Purpose 11-026 As required Wet Lay Up Resin 20-022 As required References Non Destructive Test Manual (NTM) 51-10-03, Page Block 701 51-10-19, Page Block 701 51-10-24, Page Block 401 51-10-25, Page Block 101 Procedure A and B 51-10-26, Page Block 701 51-10-28, Page Block 701 Structural Repair Manual (SRM) 51-75-12 51-77-10 51-77-11 Para 4.M.(2) 51-77-11 Para 4.A.(3) 51-77-11 Para 5. 51-77-11 Para 4.E Fig. A-GAAAA Rudder inspection Sheet 01 - Flow Chart 1, vacuum loss inspection area 1 Sheet 02 - Vacuum loss inspection - damage assessment Sheet 03 - Flow Chart 2, ELCH inspection area 2 Sheet 05 - Reporting sheet Sheet 06 - Rudder SN identification Sheet 07 - Inspection areas Sheet 08 - Typical ELCH procedure Sheet 09 - Rudder skin thickness LH Sheet 10 - Rudder skin thickness RH Sheet 11 - Rudder skin thickness LH Sheet 12 - Rudder skin thickness RH Fig. A-GACAA rudder SN - MSN reference list Sheet 01 (a) Identify the Serial Number (SN) of the rudder as shown on Fig. A-GAAAA Sheet 06

. (b) If you do not find a SN placard on the rudder, contact AIRBUS for further instructions.

DATE: Mar 16/10 SERVICE BULLETIN No.: A310-55-2049 REVISION No.: 00 - Mar 16/10 Page: 26 6

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# @A310 SERVICE BULLETIN (c) Compare the rudder SN with the rudder SNs in the rudder SN - MSN reference list Fig. A-GACAA Sheet 01

. 1 If you find a different SN against the MSN as detailed in the rudder SN - MSN reference list, contact AIRBUS for further instructions. 2 If the rudder SN is not part of the rudder SN - MSN reference list, refer to the Close-up para 3.E. No further action is necessary. 3 If the rudder is part of the rudder SN - MSN reference list with the same indicated MSN, continue with the below instructions. (d) The Technical Disposition (TD) details the location of the reworked area to be inspected and includes information about the vacuum loss vacuum loss inspection holes, if necessary. 1 For the definition of the areas to be inspected, refer to the rudder SN - MSN reference list Fig. A-GACAA Sheet 01 to find the MSN related Technical Disposition (TD) No. 2 To get the TD, refer to the SB BOOKLET-link on the index page of this Service Bulletin on the Air@Nav Engineering page in AIRBUS WORLD and use ’SB BOOKLET-TD-K45-S1-XXXXX’. For additional information, refer to SBIT SEMB 914.0808/09 3 Inspection method for reworked areas: - For reworked area astride AREA 1 and AREA 2, if TD provides vacuum loss hole location then rework must be treated as if in AREA 1 only. - For reworked area astride AREA 1 and AREA 2, if TD does not provide vacuum loss hole location then rework must be treated as if in AREA 2 only. (e) If there are only areas on the trailing edge shown as ’area 2’ on the Fig. A-GAAAA Sheet 07, to be inspected, refer to Para (g). (f) If there is another area, shown as ’area 1’ on the Fig. A-GAAAA Sheet 07, to be inspected, do the subsequent inspection in accordance with the Flow Chart Fig. AGAAAA Sheet 01 and Fig. A-GAAAA Sheet 02: 1 Do the vacuum loss inspection within 8 month after the issue of this Service Bulletin (Refer to NTM 51-10-28, Page Block 701).
a Temporarily install adhesive tape on the areas to be inspected. b Mark the grid of holes on the adhesive tape.
c CAUTION: DRILL PENETRATION INTO THE SANDWICH STRUCTURE HAS TO BE LIMITED TO 20 mm (0.8 in.) TO PREVENT INNER SKIN DAMAGE. DATE: Mar 16/10 SERVICE BULLETIN No.: A310-55-2049 REVISION No.: 00 - Mar 16/10 Page: 27 6

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# @A310 SERVICE BULLETIN Drill the vacuum loss inspection holes with DIA 1.5 mm (0.06 in.) through the outer skin only. d Do the Vacuum loss inspection (Refer to NTM 51-10-28, Page Block 701).
e In case of damage indications, report to AIRBUS on the basis of a detailed referenced damage report for further instructions before next flight. f In case of no damage indications, close the vacuum loss inspection holes as detailed in the subsequent instructions and report the result to AIRBUS within 10 days. 2 Temporary restoration of the vacuum loss inspection holes option 1:
a Close the holes with Self Adhesive Aluminium Tape 08-052 As required

or Self-Adhes. Disks 05-052 As required b Do a detailed inspection of the restored area at intervals not exceeding 4 month. Inspect the restored area for loose or lost adhesive disks or tape.
c In case of loose or lost tape ordisks, close the holes again with Self Adhesive Aluminium Tape 08-052 As required

or Self-Adhes. Disks 05-052 As required d This temporary restoration must be replaced by the permanent restoration within 4500 FC after the vacuum loss inspection. 3 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. Temporary restoration of the vacuum loss inspection holes option 2:

DATE: Mar 16/10 SERVICE BULLETIN No.: A310-55-2049 REVISION No.: 00 - Mar 16/10 Page: 28 6

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# @A310 SERVICE BULLETIN

a Before the resin injection: <1> Identify the skin thickness of the areas to be inspected, refer to the subsequent table: Rudder SN Refer to Figure HF-1122, HF-1254 TS-1362 Fig. A-GAAAA Sheet 09 and Fig. A-GAAAA Sheet 10 TS-2006, TS-2008,. TS-2010 TS-2027, TS-2030, TS-2033 TS-2043, TS-2048, TS-2049 TS-2054, TS-2055 TS-2059 TS-2061 TS-2071 thru TS-2073 TS-2082 TS-2084 thru TS-2087 Fig. A-GAAAA Sheet 11 and Fig. A-GAAAA Sheet 12

<2> If the skin thickness of the affected areas, defined by the TD, does not exceed 1.5 mm (0.06 in.), do a thermography inspection as detailed in NTM 51-10-25, Page Block 101 Procedure A and B AND/OR If the skin of the affected areas, defined by the TD, is thicker than 1.5 mm (0.06 in.), do an ultrasound inspection as detailed in NTM 51-10-24, Page Block 401. NOTE: During the ultrasound inspection, the vacuum loss inspection holes must be closed with thin adhesive tape (Material No 08-052 - basic) to prevent couplant ingress into the holes. b In case of damage indications contact AIRBUS for further instructions before next flight.
c Prepare and dry the restoration area (Refer to SRM 51-77-11 Para 4.M.(2)). d Prepare Wet Lay Up Resin 20-022 As required (Refer to SRM 51-77-11 Para 4.A.(3)). 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.
e Warm up the mixed resin to a maximum temperature of 45 ̊C (113 F).

DATE: Mar 16/10 SERVICE BULLETIN No.: A310-55-2049 REVISION No.: 00 - Mar 16/10 Page: 29 6

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# @A310 SERVICE BULLETIN

f 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 vacuum loss inspection hole. g Close the filled holes with Self Adhesive Aluminium Tape 08-052 As required

or Self-Adhes. Disks 05-052 As required h 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 in accordance with the resin manufacturer recommendations and perform a gelation test outside the restoration area. After resin gelation plus 2h, the aircraft can be released to operations again. i Within 4500 FC after the vacuum loss inspection, do the final surface restoration: <1> Remove the self adhesive tape from the restoration areas. <2> Inspect the restoration (Refer to SRM 51-77-11 Para 5.). <3> Remove any surplus resin from the border area of the restoration. Use abrasive cloth. Start with 280 grade and finish with 400 grade. <4> Clean the restoration areas with Solvent General Purpose 11-026 As required (Refer to SRM 51-77-11 Para 4.E). <5> Restore the surface protection (Refer to SRM 51-75-12). 4 Permanent restoration of the vacuum loss inspection holes:
a Before the resin injection: <1> Identify the skin thickness of the areas to be inspected, refer to the subsequent table: Rudder SN Refer to Figure HF-1122, HF-1254 TS-1362 Fig. A-GAAAA Sheet 09 and Fig. A-GAAAA Sheet 10

DATE: Mar 16/10 SERVICE BULLETIN No.: A310-55-2049 REVISION No.: 00 - Mar 16/10 Page: 30 6

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# @A310 SERVICE BULLETIN
TS-2006, TS-2008,. TS-2010 TS-2027, TS-2030, TS-2033 TS-2043, TS-2048, TS-2049 TS-2054, TS-2055 TS-2059 TS-2061 TS-2071 thru TS-2073 TS-2082 TS-2084 thru TS-2087 Fig. A-GAAAA Sheet 11 and Fig. A-GAAAA Sheet 12

<2> If the skin thickness of the affected areas, defined by the TD, does not exceed 1.5 mm (0.06 in.), do a thermography inspection as detailed in NTM 51-10-25, Page Block 101 Procedure A and B AND/OR If the skin of the affected areas, defined by the TD, is thicker than 1.5 mm (0.06 in.), do an ultrasound inspection as detailed in NTM 51-10-24, Page Block 401. NOTE: During the ultrasound inspection, the vacuum loss inspection holes must be closed with thin adhesive tape (Material No 08-052 - basic) to prevent couplant ingress into the holes. b In case of damage indications contact AIRBUS for further instructions before next flight.
c 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 (Refer to SRM 51-77-11 Para 4.M.(2)). d Prepare Wet Lay Up Resin 20-022 As required (Refer to SRM 51-77-11 Para 4.A.(3)). 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.
DATE: Mar 16/10 SERVICE BULLETIN No.: A310-55-2049 REVISION No.: 00 - Mar 16/10 Page: 31 6

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# @A310 SERVICE BULLETIN

e Warm up the mixed resin to a maximum temperature of 45 ̊C (113 F). f 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 vacuum loss inspection hole. g Close the filled holes with a self adhesive tape. h 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 in accordance with the resin manufacturer recommendations and perform a gelation test outside the restoration area. After resin gelation plus 4 h, continue with the subsequent steps: <1> Remove the self adhesive tape from the restoration areas. <2> Inspect the restoration (Refer to SRM 51-77-11 Para 5.). <3> Remove any surplus resin from the border area of the restoration. Use abrasive cloth. Start with 280 grade and finish with 400 grade. <4> Clean the restoration areas with Solvent General Purpose 11-026 As required (Refer to SRM 51-77-11 Para 4.E). <5> Restore the surface protection (Refer to SRM 51-75-12). (g) If there are areas on the trailing edge, shown as ’area 2’ on the Fig. A-GAAAA Sheet 07, to be inspected, do a special detailed inspection (ELCH) in accordance with the Flow Chart Fig. A-GAAAA Sheet 03: 1 Do the ELCH inspection within 24 month after the issue of this Service Bulletin (Refer to NTM 51-10-26, Page Block 701).
a For the ELCH inspection behind the fasteners, use one grid line with a distance of 50 mm (1.97 in.) between the inspection points, as shown on Fig. A-GAAAA Sheet 08, View D and View E, area 2. <1> The assessment criteria for the ELCH inspection behind the fasteners are: Yellow value 0.30 mm (0.012 in.) Red value 0.40 mm (0.016 in.) or the adjustment of the ELCH, refer to NTM 51-10-26, Page Block 701.

DATE: Mar 16/10 SERVICE BULLETIN No.: A310-55-2049 REVISION No.: 00 - Mar 16/10 Page: 32 6

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# @A310 SERVICE BULLETIN
b If the ELCH inspection extends ahead of the fasteners, use an inspection grid of 50 mm X 50 mm (1.97 in.) between the inspection points, as shown on Fig. A-GAAAA Sheet 08, View D and View E, area 1. <1> The assessment criteria for the ELCH inspection ahead of the fasteners are: Yellow value 0.25 mm (0.010 in.) Red value 0.35 mm (0.014 in.) For the adjustment of the ELCH, refer to NTM 51-10-26, Page Block 701. 2 In case of damage indications, re- examine the findings as per tap test inspection (Refer to NTM 51-10-03, Page Block 701 or NTM 51-10-19, Page Block 701), and contact AIRBUS for further instructions before next flight. 3 In case of no damage indications, report to AIRBUS within 10 days and do 2 additional ELCH inspections at intervals not exceeding 4500 FC and not less than 4000 FC.
a In case of damage indications during the additional ELCH inspection, reexamine the findings as per tap test inspection (Refer to NTM 51-10-03, Page Block 701 or NTM 51-10-19, Page Block 701), and contact AIRBUS for further instructions before next flight. b In case of no damage indications during the additional ELCH inspections, report to AIRBUS within 10 days. (h) Fill in the reporting sheet, refer to Fig. A-GAAAA Sheet 05

. In case of damage indications, send the inspection report with a referenced mail to: AIRTAC Customer Services AIRBUS Central Entity 1 ROND POINT MAURICE BELLONTE 31707 BLAGNAC CEDEX FRANCE Phone: +33(0)5 61 93 3400 (24 hour) Fax: +33(0)5 61 93 3500 Mailto: airtac@airbus.com and in case of damage indications or no damage indications to
DATE: Mar 16/10 SERVICE BULLETIN No.: A310-55-2049 REVISION No.: 00 - Mar 16/10 Page: 33 6

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# @A310 SERVICE BULLETIN Structure Engineering Support Customer Services - SEES1 AIRBUS Central Entity 1 ROND POINT MAURICE BELLONTE 31707 BLAGNAC CEDEX FRANCE Fax: +33(0)5 61 93 36 14 D. TEST None E. CLOSE-UP (1) Subtask 552049-942-201-001 - Close-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 29-10-00, Page Block 301 55-33-13, Page Block 401 55-40-00, Page Block 601 (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) To close the access panels, (Refer to AMM 55-33-13, 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: Mar 16/10 SERVICE BULLETIN No.: A310-55-2049 REVISION No.: 00 - Mar 16/10 Page: 34 6

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# @A310 SERVICE BULLETIN

**CONF ALL

INDICATION FOUND
CLOSE INSPECTION HOLES NO YES REPORT TO AIRBUS

TO GET FURTHER

INSTRUCTIONS BEFORE NEXT FLIGHT IDENTIFY THE RUDDER SERIAL NUMBER VIA THE PLACARD ON THE RUDDER SPAR. IN CASE OF NO EXISTING PLACARD CONTACT AIRBUS

AND REPORT TO AIRBUS WITHIN 10 DAYS

AIRBUS INSTRUCTIONS

TO BE CARRIED OUT BEFORE NEXT FLIGHT

NO FURTHER ACTION REQUIRED IN AREA 1 TEMPORARY OPTION II PERMANENT RESTORATION THERMOGRAPHY INSPECTION TEMPORARY OPTION I FREQUENT DETAILED INSPECTION OF RESTORED NOT EXCEEDING 4 MONTHS

PERMANENT RESTORATION THERMOGRAPHY INSPECTION AS PER NTM 51−10−25

CONTACT AIRBUS BEFORE FURTHER FLIGHT

IN CASE OF FINDINGS. WITHIN 4500 FC

WITHIN 4500 FC AREA, AT INTERVALS

REQUIRED BEFORE RESIN INJECTION. THERMOGRAPHY INSPECTION

RESTORE FINAL

PROTECTION OR COMPARE YOUR RUDDER SERIAL NUMBER WITH THE RUDDER SERIAL NUMBERS IN THE REFERENCE LIST

NO YES DO THE SPECIAL DETAILED INSPECTION (VACUUM LOSS) AS PER NTM 51−10−28 IN AREAS DEFINED IN SPECIFIC TECHNICAL DISPOSITION FOR EACH RUDDER NO FURTHER ACTION REQUIRED IN ACCORDANCE WITH THIS INSPECTION SB SERIAL NUMBER FOUND IN REFERENCE LIST

ULTRASOUND INSPECTION

AS PER NTM 51−10−24 AND AS PER NTM 51−10−25

CONTACT AIRBUS BEFORE FURTHER FLIGHT

IN CASE OF FINDINGS. REQUIRED BEFORE RESIN INJECTION. ULTRASOUND INSPECTION

AS PER NTM 51−10−24 AND AS PER NTM 51−10−25

CONTACT AIRBUS BEFORE FURTHER FLIGHT

IN CASE OF FINDINGS. REQUIRED BEFORE RESIN INJECTION. ULTRASOUND INSPECTION

AS PER NTM 51−10−24 AND

NOTE: FOR THE ACCOMPLISHMENT TIMESCALE. REFER TO PARA 1.E.(2) B_SB_552049_6_AAAA_01_04 Figure A-GAAAA - Sheet 01 Rudder inspection - Flow Chart 1, vacuum loss inspection area 1
DATE: Mar 16/10 SERVICE BULLETIN No.: A310-55-2049 REVISION No.: 00 - Mar 16/10 Page: 35 6

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# @A310 SERVICE BULLETIN

**CONF ALL

DAMAGE ASSESSMENT BY VACUUM LOSS INSPECTION: IF THE VACUUM LOSS INSPECTION REVEALS DAMAGE AN ADD−ON INSPECTION IN MIDFIELD DIRECTION ONLY MUST BE PERFORMED TO DEFINE THE OVERALL DAMAGE SIZE. FOR ADD−ON INSPECTION 1, DRILL ONE ADDITIONAL ROW OF INSPECTION HOLES WITH A PITCH OF 25.0mm (0.98in.) AND ONE EXTRA HOLE AT EACH END OF THE ROW PARALLEL TO THE DETECTED LEAKAGE, AS PER SKETCH BELOW. DRILL INSPECTION HOLES WITH DIAMETER 1.5mm (0.06in) THROUGH THE OUTER SKIN ONLY. WARNING: DRILL PENETRATION INTO THE SANDWICH STRUCTURE HAS TO BE LIMITED TO 20.0mm (0.79in.), TO PREVENT INNER SKIN DAMAGE. PERFORM VACUUM LOSS INSPECTION (SAME PROCEDURE AS APPLIED FOR BASIC INSPECTION), POSITION THE VACUUM CUP IN A WAY THAT ONLY ONE OF THE NEW HOLES IS COVERED BY THE CUP, DURING EACH MEASUREMENT. IF NO EXTRA LEAKAGE IS FOUND, DOCUMENT THE DAMAGE, USING THE REPORTING SHEET. IF MORE LEAKAGES ARE FOUND, PROCEED WITH ADD−ON INSPECTION 2 (AND IF REQUIRED FURTHER STEPS UNTIL THE WHOLE DAMAGE EXTEND IS DETECTED), USING THE SAME PROCEDURE AS DETAILED ABOVE. NOTE: THE OVERALL DAMAGE LENGTH AND WIDTH IS BOUNDED BY THOSE ROWS OF INSPECTION HOLES, WHICH DO NOT INDICATE A VACUUM LOSS.

OVERALL LENGTH

OVERALL

WIDTH25.0mm (0.98in.)

ADD−ON INSPECTION 1 ADD−ON INSPECTION 2 ADD−ON INSPECTION 3 BASIC INSPECTION RESULTSDIRECTION OFADD−ON INSPECTIONRESTRICTED AREA

OVERALL DAMAGE SIZE DEBONDING

DEBONDING AREA HOLES TO BE INSPECTED IN CASE OF FINDINGS. RESULTS OF VACUUM LOSS INSPECTION NO LEAKAGE LEAKAGE DETECTED WARNING: DRILLING IN THE RESTRICTED AREA CAN DAMAGE THE INNER SKIN AND IS NOT ALLOWED.

B_SB_552049_6_AAAA_02_01 Figure A-GAAAA - Sheet 02 Rudder inspection - Vacuum loss inspection - damage assessment
DATE: Mar 16/10 SERVICE BULLETIN No.: A310-55-2049 REVISION No.: 00 - Mar 16/10 Page: 36 6

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# @A310 SERVICE BULLETIN

**CONF ALL IDENTIFY THE RUDDER SERIAL NUMBER VIA THE PLACARD ON THE RUDDER SPAR. IN CASE OF NO EXISTING PLACARD CONTACT AIRBUS

INDICATION

FOUND NO YES

REPORT TO AIRBUS WITHIN 10 DAYS

REPORT TO AIRBUS

TO GET FURTHER

INSTRUCTIONS BEFORE NEXT FLIGHT RE−EXAMINE THE FINDINGS

AS PER TAP INSPECTION NTM 51−10−03 OR NTM 51−10−19 AND

INDICATION

FOUND NO YES

NO FURTHER ACTION REQUIRED IN AREA 2 AIRBUS INSTRUCTIONS TO BE CARRIED OUT BEFORE NEXT FLIGHT DO 2 ADDITIONAL ELCH INSPECTIONS AT INTERVALS NOT EXCEEDING 4500FC AND NOT LESS THAN 4000 FC

REPORT TO AIRBUS WITHIN 10 DAYS NO

YES NO FURTHER ACTION REQUIRED IN ACCORDANCE WITH THIS INSPECTION SB SERIAL NUMBER FOUND IN REFENCE LIST

FOR EACH RUDDER IN AREAS DEFINED IN SPECIFIC TECHNICAL DISPOSITION

NOTE: FOR THE ACCOMPLISHMENT TIMESCALE. REFER TO PARA 1.E.(2) DO THE REPETITIVE SPECIAL DETAILED INSPECTION (ELCH) AS PER NTM 51−10−26

B_SB_552049_6_AAAA_03_04 Figure A-GAAAA - Sheet 03 Rudder inspection - Flow Chart 2, ELCH inspection area 2
DATE: Mar 16/10 SERVICE BULLETIN No.: A310-55-2049 REVISION No.: 00 - Mar 16/10 Page: 37 6

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# @A310 SERVICE BULLETIN

**CONF ALL 

## Inspection Report **Rudder Surface Inspection as per SB in area:**

Aircraft type: MSN: Rudder S/N: Rudder P/N: Inspection date: Operator: FC: FH:
Inspection method Tap Test

Thermography

ELCH Inspection

Vacuum Loss Inspection

Inspection

Inspection UT Inspection No findings Findings as detailed by sketch and photos

No findings Findings as detailed by sketch and photos

No findings Findings as detailed by sketch and photos

No findings Findings as detailed by sketch and photos

No findings Findings as detailed by sketch and photos LH RH Rudder Side

* use sketch from the TD

B_SB_552049_6_AAAA_05_02 Figure A-GAAAA - Sheet 05 Rudder inspection - Reporting sheet
DATE: Mar 16/10 SERVICE BULLETIN No.: A310-55-2049 REVISION No.: 00 - Mar 16/10 Page: 38 6

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# @A310 SERVICE BULLETIN

**CONF ALL

NOTE: OPEN ACCESS PANEL AS PER AMM 55−33−13 P. BLOCK 201. CLOSE ACCESS PANEL AS PER AMM 55−33−13 P. BLOCK 201. POSITION OF RUDDER S/N PLACARD 

### A

Z326



## A **B** 

## B 326CL

326AL 

### C **D F**  **G**

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

B_SB_552049_6_AAAA_06_02 Figure A-GAAAA - Sheet 06 Rudder inspection - Rudder SN identification
DATE: Mar 16/10 SERVICE BULLETIN No.: A310-55-2049 REVISION No.: 00 - Mar 16/10 Page: 39 6

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# @A310 SERVICE BULLETIN

**CONF ALL

TRAILING EDGE AREA 

## AREA 2 AREA 1 OTHER AREA

50.0 mm (1.97 in) 370.0 mm (14.57 in) 50.0 mm (1.97 in) 285.0 mm (11.22 in)

SR 

## C B_SB_552049_6_AAAA_07_00 Figure A-GAAAA - Sheet 07 Rudder inspection - Inspection areas
DATE: Mar 16/10 SERVICE BULLETIN No.: A310-55-2049 REVISION No.: 00 - Mar 16/10 Page: 40 6

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# @A310 SERVICE BULLETIN

**CONF ALL

SR TYPICAL TRAILING EDGE ELCH INSPECTION FASTENERS



## AREA 1

AREA 2

75.0 mm (2.95 in) 50.0 mm (1.97 in) 75.0 mm (2.95 in) 50.0 mm (1.97 in) AREA 2 AREA 1

MINIMUM DISTANCE FROM EDGE 75.0mm (2.95in.) **NOTE:** 

### E



## D

**E**

B_SB_552049_6_AAAA_08_01 Figure A-GAAAA - Sheet 08 Rudder inspection - Typical ELCH procedure
DATE: Mar 16/10 SERVICE BULLETIN No.: A310-55-2049 REVISION No.: 00 - Mar 16/10 Page: 41 6

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# @A310 SERVICE BULLETIN

**CONF ALL

VALID FOR RUDDER NO INSPECTION T< 1.5mm (0.059in.) 

## F

B_SB_552049_6_AAAA_09_02 Figure A-GAAAA - Sheet 09 Rudder inspection - Rudder skin thickness LH
DATE: Mar 16/10 SERVICE BULLETIN No.: A310-55-2049 REVISION No.: 00 - Mar 16/10 Page: 42 6

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# @A310 SERVICE BULLETIN

**CONF ALL

VALID FOR RUDDER NO INSPECTION T< 1.5mm (0.059in.) 

## G

B_SB_552049_6_AAAA_10_02 Figure A-GAAAA - Sheet 10 Rudder inspection - Rudder skin thickness RH
DATE: Mar 16/10 SERVICE BULLETIN No.: A310-55-2049 REVISION No.: 00 - Mar 16/10 Page: 43 6

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# @A310 SERVICE BULLETIN

**CONF ALL

VALID FOR RUDDER NO INSPECTION T< 1.5mm (0.059in.) T> 1.5mm (0.059in.) 

## F

B_SB_552049_6_AAAA_11_00 Figure A-GAAAA - Sheet 11 Rudder inspection - Rudder skin thickness LH
DATE: Mar 16/10 SERVICE BULLETIN No.: A310-55-2049 REVISION No.: 00 - Mar 16/10 Page: 44 6

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# @A310 SERVICE BULLETIN

**CONF ALL

VALID FOR RUDDER NO INSPECTION T< 1.5mm (0.059in.) T> 1.5mm (0.059in.) 

## G

B_SB_552049_6_AAAA_12_00 Figure A-GAAAA - Sheet 12 Rudder inspection - Rudder skin thickness RH
DATE: Mar 16/10 SERVICE BULLETIN No.: A310-55-2049 REVISION No.: 00 - Mar 16/10 Page: 45 6

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# @A310 SERVICE BULLETIN

**CONF ALL

**Rudder−SN MSN**  **TD/K45/S1/XXXXX/2009 Side** 

**NOTE:** The subsequent rudder SN−MSN reference list reflects the rudder SN−MSN relationship at the date of the aircraft delivery.

B_SB_552049_6_ACAA_01_02 HF−1122 Spare 01546 LH HF−1254 0555 01435 LH/RH TS−1362 Spare 01547 RH TS−2006 0723 01427 RH TS−2008 0727 01426 LH/RH TS−2010 0728 01416 LH TS−2027 0742 01422 LH/RH TS−2030 0745 01514 LH TS−2033 Spare 01548 LH/RH TS−2043 0757 01415 LH/RH TS−2048 0766 01417 LH/RH TS−2049 0762 01414 RH TS−2054 0772 01428 LH TS−2055 0774 01410 RH TS−2059 0771 01411 LH/RH TS−2061 0761 01418 LH/RH TS−2071 0779 01424 LH TS−2072 0780 01433 LH/RH TS−2073 0781 01425 LH/RH TS−2082 0789 01429 LH TS−2084 0791 01431 LH/RH TS−2085 0788 01432 LH TS−2086 0792 01413 RH TS−2087 0793 01434 LH/RH

Figure A-GACAA - Sheet 01 rudder SN - MSN reference list
DATE: Mar 16/10 SERVICE BULLETIN No.: A310-55-2049 REVISION No.: 00 - Mar 16/10 Page: 46 6

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# @A310 SERVICE BULLETIN REPORTING SHEET 

### TITLE: STABILIZERS - RUDDER - A310 RUDDER DEBOND INSPECTION MODIFICATION No.: None Please complete the appropriate item (A or B): A - SB WILL BE embodied YES/NO (if NO please comment) If YES, aircraft concerned (as per SB effectivity by default) and planned dates (month/year) of embodiment:

B - SB HAS BEEN embodied on aircraft: Operator comments:
From Airline: Name/Title: Signature: Date: If operational documentation is affected (see Paragraph 1.K of this SB): If information is needed prior to next normal revision or prior to SB embodiment, please indicate required service(s): Either: Modification Operational Impact (MOI), if available YES/NO Or : Intermediate revision YES/NO Important Information: This SB will only be incorporated in your maintenance and operational documentation if this sheet is returned to Airbus and signed by a duly authorised representative. With the next feasible revision, this will result in - Updating of maintenance documentation to show pre and post SB data. - Updating of maintenance and operational documentation to show post SB data after embodiment. If this SB requires previous or simultaneous accomplishment of other SBs, Airbus shall automatically include them in the manual revisions. Refer to SIL 00-037 for detailed information. Please return this completed sheet to: AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE Attn: SDC32 Technical Data and Documentation Services FAX: (+33) 5 61 93 28 06 e-mail: sb.reporting@airbus.com or via your Resident Customer Support Office. Alternatively, SB lists via letters or fax are also accepted.

DATE: Mar 16/10 SERVICE BULLETIN No.: A310-55-2049 REVISION No.: 00 - Mar 16/10 Page: 1 6

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# @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 4 3 2 1 - Quality rating of the Accomplishment Instructions 4 3 2 1 - Quality rating of the Illustrations 4 3 2 1 - Is this SB easy to understand ? Y / N If you have had difficulties in the accomplishment of this SB please quote below the area(s) and give a short description of the issue. Planning Material Instructions X Effectivity X Kit content X Preparation X Reason X List of Materials Operator Supplied X Mod/Inspection X Manpower X Industry support X Test X References X Re-identification X Close-Up X Publication X Tooling X Illustrations Comments:

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

DATE: Mar 16/10 SERVICE BULLETIN No.: A310-55-2049 REVISION No.: 00 - Mar 16/10 Page: 1 6

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