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

# MANDATORYMANDATORYMANDATORY ATA SYSTEM: 52 

### TITLE: DOORS - NLG AFT DOORS - INSPECTION FOR CRACKS ON FWD HINGE FITTINGS **CONF ALL MODIFICATIONS None REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES During an in service inspection, an operator found cracks on the NLG aft door fitting angles. These cracks were resulting from a vibratory process under aerodynamical loads. This Service Bulletin requires a repetitive Detailed Inspection of the left and right NLG AFT doors FWD hinges, before accumulation of 4500FC since A/C first flight or since the last Fwd Hinge swan neck replacement. Accomplishment of this Inspection Service Bulletin allows monitoring the behaviour of the fittings subject to the different aerodynamical loads in the area and, if necessary, replacing them so as to avoid damage to the structure.This Service Bulletin can be done at the same time as the following Service Bulletin(s) : SBA340-52-5016. GENERAL EVALUATION EVALUATION TABLE COMPLIANCE MANDATORY (1) CANCELS INSPECTION SB NO POTENTIAL AD YES A/C OPERATION AFFECTED NO RELIABILITY AFFECTED NO PAX COMFORT AFFECTED NO COST SAVING NO LROPS AFFECTED NO STRUCTURAL LIFE EXTN NO VENDOR SB INVOLVED NO NOTE (1): Service Bulletin must be accomplished.

DATE: Feb 17/11 SERVICE BULLETIN No.: A340-52-5017 REVISION No.: 00 - Feb 17/11 Page: 1 5

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# @A340-500/600 SERVICE BULLETIN SUMMARY MATERIAL PRICE INFORMATION MATERIAL PRICE INFORMATION TABLE MATERIAL SET QTY PER A/C PRICE PER A/C (USD) MAIN PARTS Kit tool 525017T01R01 1 22,040.00 Tool Component COMPA01 2 See SB Swan Neck Component COMPA02 2 See SB Fittings Component COMPA03 2 See SB Fittings Component COMPA04 2 See SB Nut Component COMPA05 2 See SB Nut EFFECTIVITY This Service Bulletin is applicable to this (these) operator(s) :

06U 62X 70U 72W 79W ARA CES CHH DLH ETD IBE QAF QTR SAA SIA SOR TAM THA UAE VIR CONCURRENT REQUIREMENTS None REFERENCES / REPERCUSSIONS TFU None OEB None AOT None SIL None LINE MAINTENANCE AFFECTED No LIFE LIMIT None OTHER None NATURE OF THE WORK AIRCRAFT YES EQUIPMENT NO HARD NO SOFT NO OBRM NO MANPOWER Task 525017-832-801-001: Inspection TOTAL MANHOURS 5.00 ELAPSED TIME (HOURS) 5.00 Task 525017-833-801-001: Repair TOTAL MANHOURS 13.00 ELAPSED TIME (HOURS) 13.00 DATE: Feb 17/11 SERVICE BULLETIN No.: A340-52-5017 REVISION No.: 00 - Feb 17/11 Page: 2 5

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# @A340-500/600 SERVICE BULLETIN SUMMARY Task 525017-833-802-001: Repair TOTAL MANHOURS 21.00 ELAPSED TIME (HOURS) 21.00 APPENDICES Appendix 1 Appendix 2

DATE: Feb 17/11 SERVICE BULLETIN No.: A340-52-5017 REVISION No.: 00 - Feb 17/11 Page: 3 5

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

Z715

Z716 

### B



## B **A**

INSPECTION AREA HINGE No 4 SWAN NECK AND FWD, AFT FITTINGS

INSPECTION AREA HINGE No 4 SWAN NECK AND FWD, AFT FITTINGS 

## A

F_SB_525017_5_SAAA_01_01 Figure A-FSAAA - Sheet 01

DATE: Feb 17/11 SERVICE BULLETIN No.: A340-52-5017 REVISION No.: 00 - Feb 17/11 Page: 4 5

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



# MANDATORYMANDATORYMANDATORY ATA SYSTEM: 52 

### TITLE: DOORS - NLG AFT DOORS - INSPECTION FOR CRACKS ON FWD HINGE FITTINGS 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 340-541 340-542 340-642 (2) Effectivity by MSN 0371 0376 0383 0391 0394 0410 0416-0417 0426 0431 0436 0440 0445 0449 0453 0457 0460 0464 0468 0471 0475 0478 0482 0485 0488 0492 0495 0499 0514 0517 0520 0523 0531 0534 0537 0540 0543 0547 0557 0560 0563 0566 0569 0572 0575 0577 0580 0583 0586 0601 0604 0606 0608 0611 0615 0617 0619 0622 0624 0626 0628 0630 0639 0672 0677 0681 0685 0689 0694 0698 0702 0706 0710 0715 0719 0723 0727 0736 0740 0744 0748 0753 0757 0761-0768 0771 0775 0779 0783 0787 0790 0794 0798 0804 0812 0829 0837 0846 0848 0870 0886 0894 0897 0902 0910 0912 0917 0924 0929 0933 0953 0960 0972 0981 0987 0993 1005 1017 1030 1040 1079 1091 1102 1122

DATE: Feb 17/11 SERVICE BULLETIN No.: A340-52-5017 REVISION No.: 00 - Feb 17/11 Page: 1 5

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# @A340-500/600 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 06U 1091 1102 62X 0779 70U 0902 72W 0917 79W 0924 ARA 0910 0912 CES 0468 0488 0514 0577 0586 CHH 0436 0453 0475 DLH 0482 0517 0523 0537 0540 0543 0566 0569 0580 0583 0762 0763 0767 0771 0790 0794 0812 0846 0848 0897 0972 0981 0987 1005 ETD 0748 0757 0761 0783 0829 0837 0870 0929 0933 1030 1040 IBE 0431 0440 0460 0601 0604 0606 0617 0619 0672 0702 0727 0744 0960 0993 1017 1079 1122 QAF 0495 QTR 0715 0740 0766 0798 SAA 0410 0417 0426 0531 0534 0547 0557 0626 0630 SIA 0478 0492 0499 0560 0563 SOR 0886 0894 TAM 0445 0464 THA 0624 0628 0677 0681 0689 0698 0710 0719 0775 0953 UAE 0394 0457 0471 0485 0520 0572 0608 0611 0685 0694 VIR 0371 0376 0383 0391 0416 0449 0575 0615 0622 0639 0706 0723 0736 0753 0764 0765 0768 0787 0804 (4) Configuration by MSN MSN CONFIGURATION 0371 0376 0383 0391 0394 0410 0416 0417 0426 0431 0436 0440 0445 0449 0453 0457 0460 0464 0468 0471 0475 0478 0482 0485 0488 0492 0495 0499 0514 0517 0520 0523 0531 0534 0537 0540 0543 0547 0557 0560 0563 0566 0569 0572 0575 0577 0580 0583 0586 0601 0604 0606 0608 0611 0615 0617 0619 0622 0624 0626 0628 0630 0639 0672 0677 0681 0685 0689 0694 0698 0702 0706 0710 0715 0719 0723 0727 0736 0740 0744 0748 0753 0757 0761 0762 0763 0764 0765 0766 0767 0768 0771 0775 0779 0783 0787 0790 0794 0798 0804 0812 0829 0837 0846 0848 0870 0886 0894 0897 0902 0910 0912 0917 0924 0929 0933 0953 0960 0972 0981 0987 0993 1005 1017 1030 1040 1079 1091 1102 1122 001

DATE: Feb 17/11 SERVICE BULLETIN No.: A340-52-5017 REVISION No.: 00 - Feb 17/11 Page: 2 5

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# @A340-500/600 SERVICE BULLETIN (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 CMLA01 As required Consumable CMLA02 As required Component COMPA01 2 Component COMPA02 2 Component COMPA03 2 Component COMPA04 2 Component COMPA05 2 Kit tool 525017T01R01 1 B. CONCURRENT REQUIREMENTS No C. REASON (1) History During an in service inspection, an operator found cracks on the NLG aft door fitting angles. These cracks were resulting from a vibratory process under aerodynamical loads. (2) Objective/Action This Service Bulletin requires a repetitive Detailed Inspection of the left and right NLG AFT doors FWD hinges, before accumulation of 4500FC since A/C first flight or since the last Fwd Hinge swan neck replacement. (3) Advantages Accomplishment of this Inspection Service Bulletin allows monitoring the behaviour of the fittings subject to the different aerodynamical loads in the area and, if necessary, replacing them so as to avoid damage to the structure. (4) Operational/Maintenance Consequences This Service Bulletin can be done at the same time as the following Service Bulletin(s) : SB-A340-52-5016. D. DESCRIPTION To accomplish this Service Bulletin it is necessary to :

DATE: Feb 17/11 SERVICE BULLETIN No.: A340-52-5017 REVISION No.: 00 - Feb 17/11 Page: 3 5

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# @A340-500/600 SERVICE BULLETIN Task 525017-832-801-001: Inspection (1) Do an Inspection of the NLG Aft Door Fwd Hinges (LH and RH sides) Task 525017-833-801-001: Repair (1) Replace the NLG Aft Door Fwd Hinge Swan Neck of the LH Door (2) Replace the NLG Aft Door Fwd Hinge Swan Neck of the RH Door Task 525017-833-802-001: Repair (1) Replace the NLG Aft Door Fwd Hinge Fittings of the LH Door (2) Replace the NLG Aft Door Fwd Hinge Fittings of the RH Door E. COMPLIANCE (1) Classification MANDATORY: Service Bulletin must be accomplished. (2) Accomplishment Timescale The following table is representing Flow Chart 1 of Fig. A-FBDAA

.

DATE: Feb 17/11 SERVICE BULLETIN No.: A340-52-5017 REVISION No.: 00 - Feb 17/11 Page: 4 5

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# @A340-500/600 SERVICE BULLETIN
COMPLIANCE TIME (whichever occurs later) AREA TO BE INSPECTED CONDITION ACTION THRESHOLD GRACE PERIOD REPETITIVE INTERVAL NOT TO EXCEED Not applicable. Do a HFEC inspection, NTM 51-10-08 PB6 in accordance with SUBTASK 525017-280-001 001 Do an Inspection of the NLG Aft Door Fwd Hinges (LH and RH sides) Do an inspection of the NLG Aft Door Fwd Hinge Swan Neck. 4500FC since A/C first flight or since the last NLG Aft Door Fwd Hinge Swan Neck replacement. 50FC from SB issuance. If no crack finding : 500FC NLG Aft Door Fwd Hinge Swan Neck.

Crack finding on the Swan Neck Replace Swan Neck by new one on the affected NLG Aft Door(s) refer to TASK 525017-833-801 001 Repair Before next flight and start new inspection cycle. Not applicable Not applicable

Inspection of the NLG Aft Door Fwd Hinge Swan Neck (LH and RH Side) The following table is representing Flow Chart 2 of Fig. A-FBEAA

.

DATE: Feb 17/11 SERVICE BULLETIN No.: A340-52-5017 REVISION No.: 00 - Feb 17/11 Page: 5 5

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# @A340-500/600 SERVICE BULLETIN
COMPLIANCE TIME (whichever occurs later) AREA TO BE INSPECTED CONDITION ACTION THRESHOLD GRACE PERIOD REPETITIVE INTERVAL NOT TO EXCEED Not applicable Inspect in accordance with SUBTASK 525017-280-001 001 Do an Inspection of the NLG Aft Door Fwd Hinges (LH and RH sides) Do an inspection of the NLG Aft Door Fwd Hinge Fwd attachment fitting. 4500FC since A/C first flight or since the last NLG Aft Door Fwd Hinge Swan Neck Attachment Fittings replacement. 50FC from SB issuance. If no crack finding : 500FC

Crack finding on the FWD Hinge FWD Attachment Fitting as perFig. AFBBAA

. Do a HFEC inspection, NTM 51-10-08 PB6 of FWD and AFT attachment fittings on the NLG Aft Door(s) FWD Hinges where the finding(s) have been identified Before next flight Not applicable Not applicable

Do a penetrant inspection, NTM 51-80-00 PB1 on the FWD Hinge FWD and AFT attachment Fittings on the affected NLG AFT Door. or 3FC since last inspection Within maximum 20FC repeat every 3FC See NOTE 01 Crack finding on the FWD Hinge FWD Attachment Fitting and no additional crack as perFig. AFBCAA

. Do a HFEC inspection, NTM 51-10-08 PB6 on the FWD Hinge FWD and AFT attachment Fittings on the affected NLG AFT Door. 10FC since last inspection Not applicable

Within maximum 20FC repeat every 10FC See NOTE 01 NLG Aft Door Fwd Hinge Swan Neck Attachment Fittings

Crack finding on the FWD Hinge FWD attachment Fitting and additional finding as perFig. AFBCAA

. Replace both AFT and FWD fittings by new ones on the NLG Aft Door(s) FWD Hinge(s) where the finding(s) have been identified refer to TASK 525017-833-802 001 Repair Before next flight and start new inspection cycle. Not applicable Not applicable

Inspection of the NLG Aft Door Fwd Hinge Swan Neck Attachment Fittings (LH and RH Side)

DATE: Feb 17/11 SERVICE BULLETIN No.: A340-52-5017 REVISION No.: 00 - Feb 17/11 Page: 6 5

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# @A340-500/600 SERVICE BULLETIN
NOTE (01): If at 3FC or 10FC interval inspection crack evolution is detected both FWD Hinge FWD and AFT fittings must be replaced before next flight on the affected NLG AFT Door(s). In case of no additional crack finding, and once the limit of 20 FC after crack identification has been achieved, both FWD and AFT fittings must be replaced before next flight. 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 intervals given above but reference should be made to the AD for confirmation of the mandated accomplishment timescale. F. APPROVAL Approved under EASA Design Organisation Approval No. EASA21J.031. If an aircraft listed in the effectivity has a modification or repair embodied that is not of AIRBUS origin, and which affects the content of this Service Bulletin, the operator is responsible for obtaining approval by its airworthiness authority for any adaptation necessary before incorporation of the Service Bulletin. 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 525017-832-801-001: Inspection Get Access 1.00 On Aircraft Do an Inspection of the NLG Aft Door Fwd Hinges (LH and RH sides) 3.00 Close-Up 1.00 TOTAL MANHOURS 5.00 ELAPSED TIME (HOURS) 5.00 Task 525017-833-801-001: Repair Get Access 3.00 On Bench Replace the NLG Aft Door Fwd Hinge Swan Neck of the LH Door 2.00 Replace the NLG Aft Door Fwd Hinge Swan Neck of the RH Door 2.00 Close-Up 6.00 TOTAL MANHOURS 13.00 ELAPSED TIME (HOURS) 13.00 DATE: Feb 17/11 SERVICE BULLETIN No.: A340-52-5017 REVISION No.: 00 - Feb 17/11 Page: 7 5

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# @A340-500/600 SERVICE BULLETIN Task 525017-833-802-001: Repair Get Access 3.00 On Bench Replace the NLG Aft Door Fwd Hinge Fittings of the LH Door 6.00 Replace the NLG Aft Door Fwd Hinge Fittings of the RH Door 6.00 Close-Up 6.00 TOTAL MANHOURS 21.00 ELAPSED TIME (HOURS) 21.00 H. WEIGHT AND BALANCE Not Changed I. ELECTRICAL LOAD DATA Not Changed J. REFERENCES

Aircraft Maintenance Manual (AMM) 06-20-00 12-34-24 20-21-11 20-28-00 32-22-00 32-22-13 32-31-00 Consumable Material List (CML) Elec. Std. Practices Manual (ESPM) 20-55-00 Non Destructive Test Manual (NTM) 51-10-08 51-80-00 Service Bulletin (SB) SB-A340-52-5016 Standards Manual (SM) Structural Repair Manual (SRM) 51-24-00 51-42-00 51-43-00 51-44-00 51-75-11 51-75-12 K. PUBLICATION AFFECTED Impact on scheduled maintenance : Refer to Maintenance Planning Document (MPD). L. INTERCHANGEABILITY/MIXABILITY Not Applicable M. SPARES None

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# @A340-500/600 SERVICE BULLETIN
2. MATERIAL INFORMATION **CONF ALL A. MATERIAL - PRICE AND AVAILABILITY (1) Procurement Addresses Component COMPA04 Component COMPA05 Airbus Material, Logistics and Suppliers do not stock standard hardware as competetive multiple suppliers ensure access to minimum prices Airbus recommends Customers with aircraft shown in the effectivity of this Service Bulletin to send a purchase order to B/E Aerospace. The address is : B/E AEROSPACE INC CONSUMABLES MANAGEMENT 10000 NW 15TH Terrace MIAMI FL33172 USA Tel EMEA : +49(0) 40 822 285 31500 Tel US : +1 305 925 2600 Tel ASIA : +1 310 900 1300 Fax EMEA : +49 (0) 40 822 285 31010 Fax US : +1 305 507 7191 Fax ASIA : +1 310 819 1200 SITA : MIAMMCR E-Mail : AOGdesk_CMG@beaerospace.com web address : www.beconsumables.com Component COMPA01 Component COMPA02 Component COMPA03 Customers with aircraft shown in the effectivity of this Service Bulletin should send a purchase order to AIRBUS. Quote the number of this Service Bulletin. The address is : AIRBUS MATERIAL SUPPORT CENTER P.O. Box 630362 22312 Hamburg Germany (2) Price and Availability No AIRBUS kit will be provided. Parts required to accomplish this Service Bulletin are to be obtained by a Spares Purchase Order. B. INDUSTRY SUPPORT INFORMATION - INSPECTION AIRBUS will credit the manhours indicated in this Service Bulletin for inspections that are performed on aircraft under warranty at the time of such inspection. Credit will be at the operator’s agreed in-house warranty labor rate for claims received not later than 90 days after completion of the last affected aircraft of your fleet. DATE: Feb 17/11 SERVICE BULLETIN No.: A340-52-5017 REVISION No.: 00 - Feb 17/11 Page: 9 5

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# @A340-500/600 SERVICE BULLETIN
- REPAIR For aircraft with findings further to inspection as per this Service Bulletin AIRBUS will credit the material and the manhours indicated in this Service Bulletin for repair that are performed on aircraft under warranty at the time of such repair. Credit will be at the operator’s agreed in-house warranty labor rate for claims received not later than 90 days after completion of the last affected aircraft of your fleet. C. LIST OF COMPONENTS No Kit D. LIST OF MATERIALS - OPERATOR SUPPLIED (1) Consumable Materials Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Interfay Sealant 09-005A As required Sealant-Brush Consistency 09-013C As required Corrosion Inhibitingfillet Consistency 09-016B As required Solvent General Purpose 11-026 As required Corrosion Preventivetemporary Protectivecompound 15-005A As required Polyurethane Primer 16-001C As required Polyurethane Top Coat Grey 16-002D As required Polyurethane Finish Paint (for External Applic.) 16-018A As required Flexible Polyurethane 16-021 As required Primer Coat Polyurethane 16-024 As required Consumable CMLA02 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Ptfe Tape 08-041 As required Two Part Paste Adhesive 08-078 As required Interfay Sealant 09-005A As required Corrosion Inhibitingfillet Consistency 09-016B As required Solvent General Purpose 11-026 As required Corrosion Preventivetemporary Protectivecompound 15-005A As required Polyurethane Primer 16-001C As required Polyurethane Top Coat Grey 16-002D As required Polyurethane Finish Paint (for External Applic.) 16-018A As required Flexible Polyurethane 16-021 As required DATE: Feb 17/11 SERVICE BULLETIN No.: A340-52-5017 REVISION No.: 00 - Feb 17/11 Page: 10 5

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# @A340-500/600 SERVICE BULLETIN
ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Primer Coat Polyurethane 16-024 As required (2) Components Component COMPA01 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 5 F5281444000000 1 SWAN NCK Component COMPA02 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 1 F5281444120000 1 FITTING 2 F5281444220000 1 FITTING Component COMPA03 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 3 F5281444120100 1 FITTING 4 F5281444220100 1 FITTING Component COMPA04 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 13 ASNA2531-4 6 NUT 14 ASNA2532-4 12 NUT NOTE: If you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin, refer to Standards Manual (SM). The SM will give you the correct part number to part number relationship. Component COMPA05 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 13 ASNA2531-4 6 NUT 14 ASNA2532-4 1 NUT NOTE: If you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin, refer to Standards Manual (SM). The SM will give you the correct part number to part number relationship. (3) Equipment None DATE: Feb 17/11 SERVICE BULLETIN No.: A340-52-5017 REVISION No.: 00 - Feb 17/11 Page: 11 5

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# @A340-500/600 SERVICE BULLETIN
E. PARTS TO BE RE-IDENTIFIED BY OPERATOR None F. TOOLING (1) Tooling - Price and Availability (a) Procurement Addresses Kit tool 525017T01R01 Procurement to be negotiated with : AIRBUS Material, Logistics and Suppliers Weg beim Jaeger 150 D-22335 Hamburg GERMANY For ordering by internet: http://spares.airbus.com For ordering kits by fax: +49 40 50 76 25 90 For ordering of single spares by fax: +49 40 50 76 40 13 (b) Price and Availability Kit tool 525017T01R01 Cost 22,040.00 USD Availability 60 calendar days from receipt of order Procurement to be negotiated directly with AIRBUS. (2) Tools None (3) Special Tools Kit tool 525017T01R01 ITEM PART N ̊ KEYWORD QTY SEE NOTES 98F52003005000 TOOL 1

DATE: Feb 17/11 SERVICE BULLETIN No.: A340-52-5017 REVISION No.: 00 - Feb 17/11 Page: 12 5

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# @A340-500/600 SERVICE BULLETIN
3. ACCOMPLISHMENT INSTRUCTIONS Task 525017-832-801-001 - Inspection WARNING: MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS INCLUDED IN THE REFERENCED PROCEDURES. CAUTION: ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP ELECTRICAL WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY AND MECHANICALLY SERVICEABLE). WHEN YOU DO MAINTENANCE WORK, REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING, COMPONENTS AND THE WORK AREA AS CLEAN AS POSSIBLE. TO DO THIS: PUT PROTECTION, SUCH AS PLASTIC SHEETING, CLOTHS, ETC; AS NECESSARY ON 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. Task Associated Data Zone From 715 to 716 Manpower TOTAL MANHOURS 5.00 ELAPSED TIME (HOURS) 5.00 A. GENERAL (1) Subtask 525017-910-001-001 - Standard Practices Work Zones and Access Panels Zone Access/Work location From 715 To 716 Manpower Resources Skills AIRFRAME Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Solvent General Purpose 11-026 As required
DATE: Feb 17/11 SERVICE BULLETIN No.: A340-52-5017 REVISION No.: 00 - Feb 17/11 Page: 13 5

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# @A340-500/600 SERVICE BULLETIN
References Aircraft Maintenance Manual (AMM) 06-20-00, Page Block 001 (a) For the identification of the Zones, refer to AMM 06-20-00, Page Block 001. (b) Clean the surface with Solvent General Purpose 11-026 As required (2) Subtask 525017-839-001-001 - 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 525017-941-001-001 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 12-34-24-860-802 Task 32-22-00-010-801 (a) Make sure that the aircraft is electrically grounded (Refer to AMM Task 12-34-24-860-802). (b) Put the access platform(s) in position. (c) Open the NLG doors (Refer to AMM Task 32-22-00-010-801). C. PROCEDURE (1) Subtask 525017-280-001-001 - Do an Inspection of the NLG Aft Door Fwd Hinges (LH and RH sides) Work Zones and Access Panels Zone Access/Work location From 715 To 716

DATE: Feb 17/11 SERVICE BULLETIN No.: A340-52-5017 REVISION No.: 00 - Feb 17/11 Page: 14 5

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# @A340-500/600 SERVICE BULLETIN Manpower Resources Manhours 3.00 Minimum number of person 1 Subtask elapsed time 3.00 Skills NON SPECIFIC NON DESTRUCTIVE TESTING References Non Destructive Test Manual (NTM) 51-10-08 51-80-00 Fig. A-FBAAA Inspection of the NLG Aft Door Fwd Hinge Swan Neck Sheet 01 Sheet 02 Fig. A-FBBAA Inspection of the NLG Aft Door Fwd Hinge Fwd Attachment Fitting Sheet 01 Sheet 02 Fig. A-FBCAA Inspection of the NLG Aft Door Fwd Hinge Fwd and Aft Attachment Fittings Sheet 01 Sheet 02 Fig. A-FBDAA Flow Chart 1 Sheet 01 Fig. A-FBEAA Flow Chart 2 Sheet 01 Sheet 02 (a) Do an Inspection of the NLG Aft Door Fwd Hinge Swan neck (LH and RH Sides). 1 For the inspection area, refer to Fig. A-FBAAA

. 2 Do a Special Detailed Inspection of the NLG Aft Door Fwd Hinge Swan neck (LH and RH Sides), refer to flow chart Fig. A-FBDAA

. a For the High-Frequency Eddy Current (HFEC) Inspection, refer to NTM 51-10-08. 3 For inspection report, refer to Appendix 1 . (b) Do an Inspection of the NLG Aft Door Fwd Hinge Fwd Attachment fitting (LH and RH Sides). 1 For the inspection area, refer to Fig. A-FBBAA, Fig. A-FBCAA

. 2 Do a Detailed Inspection of the NLG Aft Door Fwd Hinge Fwd Attachment Fitting ( LH and RH Sides), refer to flow chart Fig. A-FBEAA

. 3 In case of finding, do a HFEC Inspection per NTM 51-10-08 PB06 of the FWD and AFT Attachment Fittings of the FWD Hinge of the NLG Aft Door.

DATE: Feb 17/11 SERVICE BULLETIN No.: A340-52-5017 REVISION No.: 00 - Feb 17/11 Page: 15 5

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# @A340-500/600 SERVICE BULLETIN
4 If no additional findings, do a Special Detailed Inspection of the NLG Aft Door FWD Hinge FWD and AFT Attachment Fittings : a For the High-Frequency Eddy Current (HFEC) Inspection, refer to NTM 51-10-08. b For the Penetrant Inspection, (Refer to NTM 51-80-00). 5 For inspection report, refer to Appendix 2 . D. TEST None E. CLOSE-UP (1) Subtask 525017-942-001-001 - Close-up Work Zones and Access Panels Zone Access/Work location From 715 To 716 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 32-22-00-410-801 (a) Close the NLG doors (Refer to AMM Task 32-22-00-410-801). (b) Make sure that the work areas are clean and clear of tools and other items of equipment. (c) Remove the access platform(s). (d) Restore the systems and the aircraft to normal operating condition.

DATE: Feb 17/11 SERVICE BULLETIN No.: A340-52-5017 REVISION No.: 00 - Feb 17/11 Page: 16 5

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# @A340-500/600 SERVICE BULLETIN Task 525017-833-801-001 - Repair WARNING: MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS INCLUDED IN THE REFERENCED PROCEDURES. CAUTION: ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP ELECTRICAL WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY AND MECHANICALLY SERVICEABLE). WHEN YOU DO MAINTENANCE WORK, REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING, COMPONENTS AND THE WORK AREA AS CLEAN AS POSSIBLE. TO DO THIS: PUT PROTECTION, SUCH AS PLASTIC SHEETING, CLOTHS, ETC; AS NECESSARY ON 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. Task Associated Data Zone 715 Manpower TOTAL MANHOURS 13.00 ELAPSED TIME (HOURS) 13.00 A. GENERAL (1) Subtask 525017-910-002-001 - Standard Practices Manpower Resources Skills NON SPECIFIC Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Solvent General Purpose 11-026 As required Corrosion Preventive temporary Protective compound 15-005A As required Polyurethane Primer 16-001C As required Polyurethane Top Coat Grey 16-002D As required

DATE: Feb 17/11 SERVICE BULLETIN No.: A340-52-5017 REVISION No.: 00 - Feb 17/11 Page: 17 5

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# @A340-500/600 SERVICE BULLETIN
ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Polyurethane Finish Paint (for External Applic.) 16-018A As required Flexible Polyurethane 16-021 As required Primer Coat Polyurethane 16-024 As required References Aircraft Maintenance Manual (AMM) 06-20-00, Page Block 001 Task 20-21-11-911-801 Consumable Material List (CML) Standards Manual (SM) Structural Repair Manual (SRM) 51-24-00 51-42-00 51-43-00 51-44-00 51-75-11 51-75-12 (a) For the specification of the materials (Mat. No.) that you must use in this Service Bulletin, refer to Consumable Materials List (CML) . (b) Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. (c) For the identification of the Zones, refer to AMM 06-20-00, Page Block 001. (d) Put all the retained hardware in identified plastic bags to the related unit. (e) For the alternative and substitute fasteners, refer to SRM 51-43-00. (f) Remove and install the fasteners, refer to SRM 51-42-00. (g) Drill and deburr the holes refer to SRM 51-44-00. (h) To torque tighten the standard threaded fasteners, refer to AMM Task 20-21-11-911-801. (i) Apply the sealant refer to SRM 51-24-00. (j) Use a non-metallic spatula to remove the sealant and clean the areas with : Solvent General Purpose 11-026 As required

DATE: Feb 17/11 SERVICE BULLETIN No.: A340-52-5017 REVISION No.: 00 - Feb 17/11 Page: 18 5

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# @A340-500/600 SERVICE BULLETIN (k) Renew the protection finish refer to SRM 51-75-11 and SRM 51-75-12 with : 1 Internal area : Polyurethane Primer 16-001C As required Polyurethane Top Coat Grey 16-002D As required
OR Polyurethane Primer 16-001C As required
Flexible Polyurethane 16-021 As required
2 External area : Polyurethane Primer 16-001C As required
Primer Coat Polyurethane 16-024 As required Polyurethane Finish Paint (for External Applic.) 16-018A As required
(l) Apply the temporary protection for the internal area : Corrosion Preventive temporary Protective compound 15-005A As required

(2) Subtask 525017-839-002-001 - 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 525017-941-002-001 - Job Set-up Manpower Resources Skills NON SPECIFIC
DATE: Feb 17/11 SERVICE BULLETIN No.: A340-52-5017 REVISION No.: 00 - Feb 17/11 Page: 19 5

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# @A340-500/600 SERVICE BULLETIN
References Aircraft Maintenance Manual (AMM) Task 12-34-24-860-802 (a) Make sure that the aircraft is electrically grounded refer to AMM Task 12-34-24-860-802. (b) Put access platform(s) in position. (2) Subtask 525017-010-001-001 - Remove for Bench Work (LH Side) Work Zones and Access Panels Zone Access/Work location 715 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 32-22-13-000-801 (a) Remove the NLG LH Aft Door assy refer to AMM Task 32-22-13-000-801. (3) Subtask 525017-010-002-001 - Remove for Bench Work (RH Side) Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 32-22-13-000-801 (a) Remove the NLG RH Aft Door assy refer to AMM Task 32-22-13-000-801. C. PROCEDURE (1) Subtask 525017-960-001-001 - Replace the NLG Aft Door Fwd Hinge Swan Neck of the LH Door Manpower Resources Manhours 2.00 Minimum number of person 1 Subtask elapsed time 2.00 Skills AIRFRAME Material necessary to do the job Component COMPA01 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 5 F5281444000000 1 SWAN NCK

DATE: Feb 17/11 SERVICE BULLETIN No.: A340-52-5017 REVISION No.: 00 - Feb 17/11 Page: 20 5

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# @A340-500/600 SERVICE BULLETIN Component COMPA05 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 13 ASNA2531-4 6 NUT 14 ASNA2532-4 1 NUT Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Interfay Sealant 09-005A As required Sealant-Brush Consistency 09-013C As required Corrosion Inhibiting fillet Consistency 09-016B As required
Kit tool 525017T01R01 ITEM PART N ̊ KEYWORD QTY SEE NOTES 98F52003005000 TOOL 1 References Aircraft Maintenance Manual (AMM) 20-28-00 Fig. A-FCBAA Replacement of the NLG Aft Door Fwd Hinge Swan Neck Sheet 01 Sheet 02 Sheet 03 (a) Remove the Swan neck Item (5). Refer to Fig Fig. A-FCBAA

. 1 Disconnect bonding attached with : 1 Nut Item (14) Discard 1 Washer Item (18) Retain 1 Bolt Item (11) Retain and 1 Nut Item (13) Discard 1 Washer Item (15) Retain 1 Bolt Item (17) Retain 2 Remove : 1 Swan Neck Item (5) Discard attached with : DATE: Feb 17/11 SERVICE BULLETIN No.: A340-52-5017 REVISION No.: 00 - Feb 17/11 Page: 21 5

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# @A340-500/600 SERVICE BULLETIN 5 Bolt Item (10) Retain 5 NUT Item (13) Discard 3 Remove the sealant (b) Temporarily, put in position the new Swan neck Item 5 on the tool 98F52003005000 Tool 1 and do the different steps in accordance with the user guide delivered in the kit tool. (c) Drill holes on the Swan neck to match the existing holes on the fittings. (d) Ream holes on the Swan neck to the final diameter given in Fig. A-FCBAA Sheet 02

. (e) Installation of the Swan neck refer to Fig. A-FCBAA Sheet 03 1 Apply between the Swan neck and the fittings Interfay Sealant 09-005A As required Corrosion Inhibiting fillet Consistency 09-016B As required

2 Install : 1 Swan Neck F5281444000000 Item 5 with 5 Bolt Item (10) Retained at removal 5 Nut ASNA2531-4 Item 13 3 Connect bonding as per AMM 20-28-00: 1 Bolt Item (17) Retained at removal 1 Washer Item (15) Retained at removal 1 Nut ASNA2531-4 Item 13 and 1 Bolt Item (11) Retained at removal

DATE: Feb 17/11 SERVICE BULLETIN No.: A340-52-5017 REVISION No.: 00 - Feb 17/11 Page: 22 5

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# @A340-500/600 SERVICE BULLETIN 1 Washer Item (18) Retained at removal 1 Nut ASNA2532-4 Item 14 Wet assembly for Item (10), (11) and (17) with : Sealant-Brush Consistency 09-013C As required (2) Subtask 525017-960-002-001 - Replace the NLG Aft Door Fwd Hinge Swan Neck of the RH Door Manpower Resources Manhours 2.00 Minimum number of person 1 Subtask elapsed time 2.00 Skills AIRFRAME Material necessary to do the job Component COMPA01 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 5 F5281444000000 1 SWAN NCK Component COMPA05 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 13 ASNA2531-4 6 NUT 14 ASNA2532-4 1 NUT Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Interfay Sealant 09-005A As required Sealant-Brush Consistency 09-013C As required Corrosion Inhibiting fillet Consistency 09-016B As required
Kit tool 525017T01R01 ITEM PART N ̊ KEYWORD QTY SEE NOTES 98F52003005000 TOOL 1 References Aircraft Maintenance Manual (AMM) 20-28-00

DATE: Feb 17/11 SERVICE BULLETIN No.: A340-52-5017 REVISION No.: 00 - Feb 17/11 Page: 23 5

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# @A340-500/600 SERVICE BULLETIN
References Fig. A-FCBAA Replacement of the NLG Aft Door Fwd Hinge Swan Neck Sheet 01 Sheet 02 Sheet 03 (a) Remove the Swan Neck Item (5) Refer to Fig. A-FCBAA

. 1 Disconnect bonding attached with : 1 Nut Item (14) Discard 1 Washer Item (18) Retain 1 Bolt Item (11) Retain and 1 Nut Item (13) Discard 1 Washer Item (15) Retain 1 Bolt Item (17) Retain 2 Remove : 1 Swan Neck Item (5) Discard attached with : 5 Bolt Item (10) Retain 5 NUT Item (13) Discard 3 Remove the sealant. (b) Temporarily, put in position the new Swan neck Item 5 on the tool 98F52003005000 Tool 1 and do the different steps in accordance with the user guide delivered in the kit tool. (c) Drill holes on the Swan Neck to match the existing holes on the fittings. (d) Ream holes on the Swan Neck to the final diameter given in Fig. A-FCBAA Sheet 02

. (e) Installation of the Swan Neck refer to Fig. A-FCBAA Sheet 03

. 1 Apply between the Swan Neck and the fittings. Interfay Sealant 09-005A As required
DATE: Feb 17/11 SERVICE BULLETIN No.: A340-52-5017 REVISION No.: 00 - Feb 17/11 Page: 24 5

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# @A340-500/600 SERVICE BULLETIN Corrosion Inhibiting fillet Consistency 09-016B As required

2 Install : 1 Swan Neck F5281444000000 Item 5 with 5 Bolt Item (10) Retained at removal 5 Nut ASNA2531-4 Item 13 3 Connect bonding as per AMM 20-28-00 1 Bolt Item (17) Retained at removal 1 Washer Item (15) Retained at removal 1 Nut ASNA2531-4 Item 13 and 1 Bolt Item (11) Retained at removal 1 Washer Item (18) Retained at removal 1 Nut ASNA2532-4 Item 14 Wet assembly for Item (10), (11) and (17) with : Sealant-Brush Consistency 09-013C As required
D. TEST (1) Subtask 525017-710-002-001 - Operational Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 32-31-00-710-807 Do the operational test of the NLG Normal Extension and Retraction (Refer to AMM Task 32-31-00-710-807) after the following paragraph E.CLOSE-UP (1)(a) and (2)(a).

DATE: Feb 17/11 SERVICE BULLETIN No.: A340-52-5017 REVISION No.: 00 - Feb 17/11 Page: 25 5

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# @A340-500/600 SERVICE BULLETIN
E. CLOSE-UP (1) Subtask 525017-410-001-001 - Install Items Removed for Bench Work LH Side Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 32-22-13-400-801 (a) Install the NLG LH AFT Door assy (Refer to AMM Task 32-22-13-400-801). (b) Do the SUBTASK 525017-942-001 001 Close-up . (2) Subtask 525017-410-002-001 - Install Items Removed for Bench Work RH Side Manpower Resources Skills AIRFRAME References Aircraft Maintenance Manual (AMM) Task 32-22-13-400-801 (a) Install the NLG RH AFT Door assy (Refer to AMM Task 32-22-13-400-801). (b) Do the SUBTASK 525017-942-001 001 Close-up .

DATE: Feb 17/11 SERVICE BULLETIN No.: A340-52-5017 REVISION No.: 00 - Feb 17/11 Page: 26 5

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# @A340-500/600 SERVICE BULLETIN Task 525017-833-802-001 - Repair WARNING: MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS INCLUDED IN THE REFERENCED PROCEDURES. CAUTION: ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP ELECTRICAL WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY AND MECHANICALLY SERVICEABLE). WHEN YOU DO MAINTENANCE WORK, REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING, COMPONENTS AND THE WORK AREA AS CLEAN AS POSSIBLE. TO DO THIS: PUT PROTECTION, SUCH AS PLASTIC SHEETING, CLOTHS, ETC; AS NECESSARY ON 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. Task Associated Data Zone 715 Manpower TOTAL MANHOURS 21.00 ELAPSED TIME (HOURS) 21.00 A. GENERAL (1) Subtask 525017-910-003-001 - Standard Practices Work Zones and Access Panels Zone Access/Work location 715 Manpower Resources Skills NON SPECIFIC Material necessary to do the job Consumable CMLA02 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Solvent General Purpose 11-026 Corrosion Preventivetemporary Protectivecompound 15-005A

DATE: Feb 17/11 SERVICE BULLETIN No.: A340-52-5017 REVISION No.: 00 - Feb 17/11 Page: 27 5

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# @A340-500/600 SERVICE BULLETIN
ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Polyurethane Primer 16-001C Polyurethane Top Coat Grey 16-002D Polyurethane Finish Paint (for External Applic.) 16-018A Flexible Polyurethane 16-021 Primer Coat Polyurethane 16-024 References Aircraft Maintenance Manual (AMM) 06-20-00, Page Block 001 Task 20-21-11-911-801 Consumable Material List (CML) Standards Manual (SM) Structural Repair Manual (SRM) 51-24-00 51-42-00 51-43-00 51-44-00 51-75-11 51-75-12 (a) For the specification of the materials (Mat. No.) that you must use in this Service Bulletin, refer to Consumable Materials List (CML) . (b) Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. (c) For the identification of the Zones, refer to AMM 06-20-00, Page Block 001. (d) Put all the retained hardware in identified plastic bags to the related unit. (e) For the alternative and substitute fasteners, refer to SRM 51-43-00. (f) Remove and install the fasteners, refer to SRM 51-42-00. (g) Drill and deburr the holes refer to SRM 51-44-00. (h) To torque tighten the standard threaded fasteners, refer to AMM Task 20-21-11-911-801. (i) Apply the sealant refer to SRM 51-24-00. (j) Use a non-metallic spatula to remove the sealant and clean the areas with : Solvent General Purpose 11-026 As required

DATE: Feb 17/11 SERVICE BULLETIN No.: A340-52-5017 REVISION No.: 00 - Feb 17/11 Page: 28 5

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# @A340-500/600 SERVICE BULLETIN (k) Renew the protection finish refer to SRM 51-75-11 and SRM 51-75-12 with : 1 Internal area : Polyurethane Primer 16-001C As required Polyurethane Top Coat Grey 16-002D As required
OR Polyurethane Primer 16-001C As required
Flexible Polyurethane 16-021 As required
2 External area : Polyurethane Primer 16-001C As required
Primer Coat Polyurethane 16-024 As required Polyurethane Finish Paint (for External Applic.) 16-018A As required
(l) Apply the temporary protection for the internal area : Corrosion Preventivetemporary Protectivecompound 15-005A As required

B. PREPARATION (1) Subtask 525017-941-003-001 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 12-34-24-860-802 (a) Make sure that the aircraft is electrically grounded refer to AMM Task 12-34-24-860-802. (b) Put access platform(s) in position.

DATE: Feb 17/11 SERVICE BULLETIN No.: A340-52-5017 REVISION No.: 00 - Feb 17/11 Page: 29 5

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# @A340-500/600 SERVICE BULLETIN (2) Subtask 525017-010-003-001 - Remove for Bench Work (LH Side) Work Zones and Access Panels Zone Access/Work location 715 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 32-22-13-000-801 (a) Remove the NLG LH Aft Door assy refer to AMM Task 32-22-13-000-801. (3) Subtask 525017-010-004-001 - Remove for Bench Work (RH Side) Work Zones and Access Panels Zone Access/Work location 715 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 32-22-13-000-801 (a) Remove the NLG RH Aft Door assy refer to AMM Task 32-22-13-000-801. C. PROCEDURE (1) Subtask 525017-960-003-001 - Replace the NLG Aft Door Fwd Hinge Fittings of the LH Door Manpower Resources Manhours 6.00 Minimum number of person 1 Subtask elapsed time 6.00 Skills AIRFRAME Material necessary to do the job Component COMPA02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 1 F5281444120000 1 FITTING 2 F5281444220000 1 FITTING

DATE: Feb 17/11 SERVICE BULLETIN No.: A340-52-5017 REVISION No.: 00 - Feb 17/11 Page: 30 5

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# @A340-500/600 SERVICE BULLETIN Component COMPA04 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 13 ASNA2531-4 6 NUT 14 ASNA2532-4 12 NUT Consumable CMLA02 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Ptfe Tape 08-041 As required Two Part Paste Adhesive 08-078 As required Interfay Sealant 09-005A As required Corrosion Inhibiting fillet Consistency 09-016B As required
References Aircraft Maintenance Manual (AMM) 20-28-00 Fig. A-FCAAA Replacement of the NLG Aft Door Fwd Hinge Fwd and Aft Attachment Fittings Sheet 01 Sheet 02 Sheet 03 (a) Replace the NLG Aft Door Fwd Hinge Aft Fitting of the LH Door refer to Fig. AFCAAA

. 1 Disconnect bonding attached with 1 Nut Item (13) Discard 1 Washer Item (15) Retain 1 Bolt Item (17) Retain 2 Remove Fasteners of the Fitting Item (2) refer to Fig. A-FCAAA Sheet 02

. 5 Bolt Item (10) Retain 5 NUT Item (13) Discard 3 Mark the position around of the Fitting Item (2). 4 Remove : 8 Nut Item (14) Discard 8 Bolt Item (11) Retain 5 Remove : 1 Fitting Item (2)
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# @A340-500/600 SERVICE BULLETIN
6 Remove the sealant. 7 Temporarily put in position the new Fitting Item 2. a Make sure that the alignment is in accordance with the marked position. 8 Drill the Fitting Item 2. a Drill holes on the Fitting Item 2 to match the existing holes of the Swan Neck and the Fwd fitting. b Drill holes on the Fitting Item 2 and deburr the holes. c Ream holes on the Fitting Item 2 to the final diameter given Fig. AFCAAA Sheet 02

. 9 Apply the aluminium filler between the Fitting Item 2 and the door. Ptfe Tape 08-041 As required Two Part Paste Adhesive 08-078 As required

a Put in position the Fitting Item 2. b Let the aluminium filler dry. c Remove Fitting Item 2. d Remove the aluminium filler in the holes of the Fitting Item 2. e Remove the tape. 10 Install the Fitting 1 Fitting F5281444220000 Item 2 refer to Fig. A-FCAAA Sheet 03

. a Apply between Fitting Item 2 and Swan Neck: Interfay Sealant 09-005A As required Corrosion Inhibiting fillet Consistency 09-016B As required
b Install : In order to permit a correct alignment of the new fittings

DATE: Feb 17/11 SERVICE BULLETIN No.: A340-52-5017 REVISION No.: 00 - Feb 17/11 Page: 32 5

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# @A340-500/600 SERVICE BULLETIN <1> Install only : 8 Bolt Item (11) Retained at removal 8 Nut ASNA2532-4 Item 14 (b) Replace the NLG Aft Door Fwd Hinge Fwd Fitting of the LH Door refer to Fig. AFCAAA

. 1 Mark the position around of the Fwd Fitting Item (1). 2 Remove fasteners 4 Nut Item (14) Discard 4 Bolt Item (11) Retain 3 Remove : 1 Fitting Item (1) 4 Remove the sealant. 5 Temporarily put in position the new Fwd Fitting Item 1. a Make sure that the alignment is in accordance with the marked position. 6 Drill the Fitting Item 1. a Drill holes on the Fitting Item 1 to match the existing holes of the Swan Neck and the Aft fitting. b Drill holes on the Fitting Item 1 and deburr the holes. c Ream holes on the Fitting Item 1 to the final diameter given Fig. AFCAAA Sheet 02

. 7 Apply the aluminium filler between the Fitting Item 1 and the door. Ptfe Tape 08-041 As required Two Part Paste Adhesive 08-078 As required

a Put in position the Fitting Item 1. b Let the aluminium filler dry. c Remove Fitting Item 1. d Remove the aluminium filler in the holes of the Fitting Item 1. e Remove the tape. DATE: Feb 17/11 SERVICE BULLETIN No.: A340-52-5017 REVISION No.: 00 - Feb 17/11 Page: 33 5

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# @A340-500/600 SERVICE BULLETIN
8 Install the Fitting 1 Fitting F5281444120000 Item 1 refer to Fig. A-FCAAA Sheet 03

. a Apply between Fitting Item 1 and Swan Neck: Interfay Sealant 09-005A As required Corrosion Inhibiting fillet Consistency 09-016B As required
b Install fasteners : Do not forget to install electrical bounding as per AMM 20-28-00. 4 Bolt Item (11) Retained at removal 4 Nut ASNA2532-4 Item 14 and 5 Bolt Item (10) Retained at removal 1 Bolt Item (17) Retained at removal 1 Washer Item (15) Retained at removal With 6 Nut ASNA2531-4 Item 13

(2) Subtask 525017-960-004-001 - Replace the NLG Aft Door Fwd Hinge Fittings of the RH Door Manpower Resources Manhours 6.00 Minimum number of person 1 Subtask elapsed time 6.00 Skills AIRFRAME Material necessary to do the job Component COMPA03 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 3 F5281444120100 1 FITTING DATE: Feb 17/11 SERVICE BULLETIN No.: A340-52-5017 REVISION No.: 00 - Feb 17/11 Page: 34 5

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# @A340-500/600 SERVICE BULLETIN
ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 4 F5281444220100 1 FITTING Component COMPA04 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 13 ASNA2531-4 6 NUT 14 ASNA2532-4 12 NUT Consumable CMLA02 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Ptfe Tape 08-041 As required Two Part Paste Adhesive 08-078 As required Interfay Sealant 09-005A As required Corrosion Inhibiting fillet Consistency 09-016B As required
References Aircraft Maintenance Manual (AMM) 20-28-00 Fig. A-FCAAA Replacement of the NLG Aft Door Fwd Hinge Fwd and Aft Attachment Fittings Sheet 01 Sheet 02 Sheet 03 (a) Replace the NLG Aft Door Fwd Hinge Aft Fitting of the RH Door refer to Fig. AFCAAA

. 1 Disconnect bonding attached with 1 Nut Item (13) Discard 1 Washer Item (15) Retain 1 Bolt Item (17) Retain 2 Remove Fasteners of the Fitting Item (4) Refer to Fig. A-FCAAA Sheet 02

. 5 Bolt Item (10) Retain 5 NUT Item (13) Discard 3 Mark the position around of the Fitting Item (4). 4 Remove : 8 Nut Item (14) Discard 8 Bolt Item (11) Retain
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# @A340-500/600 SERVICE BULLETIN
5 Remove : 1 Fitting Item (4) 6 Remove the sealant. 7 Temporarily put in position the new Fitting Item 4. a Make sure that the alignment is in accordance with the marked position. 8 Drill the Fitting Item 4. a Drill holes on the Fitting Item 4 to match the existing holes of the Swan Neck and the Fwd fitting. b Drill holes on the Fitting Item 4 and deburr the holes. c Ream holes on the Fitting Item 4 to the final diameter given Fig. AFCAAA Sheet 02

. 9 Apply the aluminium filler between the Fitting Item 4 and the door. Ptfe Tape 08-041 As required Two Part Paste Adhesive 08-078 As required

a Put in position the Fitting Item 4. b Let the aluminium filler dry. c Remove Fitting Item 4. d Remove the aluminium filler in the holes of the Fitting Item 4. e Remove the tape. 10 Install the Fitting 1 Fitting F5281444220100 Item 4 refer to Fig. A-FCAAA Sheet 03

. a Apply between Fitting Item 4 and Hinge : Interfay Sealant 09-005A As required Corrosion Inhibiting fillet Consistency 09-016B As required
b Install : In order to permit a correct alignment of the new fittings.
DATE: Feb 17/11 SERVICE BULLETIN No.: A340-52-5017 REVISION No.: 00 - Feb 17/11 Page: 36 5

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# @A340-500/600 SERVICE BULLETIN <1> Install only the fasteners 8 Bolt Item (11) Retained at removal 8 Nut ASNA2532-4 Item 14 (b) Replace the NLG Aft Door Fwd Hinge Fwd Fitting of the RH Door refer to Fig. AFCAAA

. 1 Mark the position around of the Fitting Item (3). 2 Remove fasteners : 4 Nut Item (14) Discard 4 Bolt Item (11) Retain 3 Remove : 1 Fitting Item (3) 4 Remove the sealant. 5 Temporarily put in position the new Fwd Fitting Item 3. a Make sure that the alignment is in accordance with the marked position. 6 Drill the Fitting Item 3. a Drill holes on the Fitting Item 3 to match the existing holes of the Swan Neck and the Aft Fitting. b Drill holes on the Fitting Item 3 and deburr the holes. c Ream holes on the Fitting Item 3 to the final diameter given Fig. AFCAAA Sheet 02

. 7 Apply the aluminium filler between the Fitting Item 3 and the door. Ptfe Tape 08-041 As required Two Part Paste Adhesive 08-078 As required

a Put in position the Fitting Item 3. b Let the aluminium filler dry. c Remove fitting Item 3. d Remove the aluminium filler in the holes of the Fitting Item 3. e Remove the tape. DATE: Feb 17/11 SERVICE BULLETIN No.: A340-52-5017 REVISION No.: 00 - Feb 17/11 Page: 37 5

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# @A340-500/600 SERVICE BULLETIN
8 Install the Fitting 1 Fitting F5281444120100 Item 3 Refer to Fig. A-FCAAA Sheet 03

. a Apply between Fitting Item 3 and Hinge : Interfay Sealant 09-005A As required Corrosion Inhibiting fillet Consistency 09-016B As required
b Install fasteners : Do not forget to install electrical bounding as per AMM 20-28-00. 4 Bolt Item (11) Retained at removal 4 Nut ASNA2532-4 Item 14 and 5 Bolt Item (10) Retained at removal 1 Bolt Item (17) Retained at removal 1 Washer Item (15) Retained at removal With 6 Nut ASNA2531-4 Item 13 D. TEST (1) Subtask 525017-710-003-001 - Operational Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 32-31-00-710-807 Do the operational test of the NLG Normal Extension and Retraction (Refer to AMM Task 32-31-00-710-807) after the following paragraph E.CLOSE-UP (1)(a) and (2)(a). NOTE: This operational test is not necessary if the task TASK 525017-833-802 001 Repair of this Service Bulletin has been done without deviation and if the removed AFT NLG doors are installed back on the same aircraft. DATE: Feb 17/11 SERVICE BULLETIN No.: A340-52-5017 REVISION No.: 00 - Feb 17/11 Page: 38 5

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# @A340-500/600 SERVICE BULLETIN
E. CLOSE-UP (1) Subtask 525017-410-003-001 - Install Items Removed for Bench Work LH Side Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 32-22-13-400-801 (a) Install the NLG LH Aft Door assy refer to AMM Task 32-22-13-400-801. (b) Do the SUBTASK 525017-942-001 001 Close-up (2) Subtask 525017-410-004-001 - Install Items Removed for Bench Work RH Side Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 32-22-13-400-801 (a) Install the NLG RH Aft Door assy refer to AMM Task 32-22-13-400-801. (b) Do the SUBTASK 525017-942-001 001 Close-up

DATE: Feb 17/11 SERVICE BULLETIN No.: A340-52-5017 REVISION No.: 00 - Feb 17/11 Page: 39 5

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# @A340-500/600 SERVICE BULLETIN

**CONF ALL

Z715

Z716

LH SIDE SHOWN RH SIDE SYMMETRICAL 

### B **B**

**C** 

## B **A A**  Z120

F_SB_525017_5_BAAA_01_00 Figure A-FBAAA - Sheet 01 Inspection of the NLG Aft Door Fwd Hinge Swan Neck

DATE: Feb 17/11 SERVICE BULLETIN No.: A340-52-5017 REVISION No.: 00 - Feb 17/11 Page: 40 5

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# @A340-500/600 SERVICE BULLETIN

**CONF ALL

F_SB_525017_5_BAAA_02_00 

### D 

## C

**D** AREAS TO BE INSPECTED

Figure A-FBAAA - Sheet 02 Inspection of the NLG Aft Door Fwd Hinge Swan Neck

DATE: Feb 17/11 SERVICE BULLETIN No.: A340-52-5017 REVISION No.: 00 - Feb 17/11 Page: 41 5

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# @A340-500/600 SERVICE BULLETIN

**CONF ALL

Z715

Z716

LH SIDE SHOWN RH SIDE SYMMETRICAL 

### B **B**

**C** 

## B **A A**  Z120

F_SB_525017_5_BBAA_01_00 Figure A-FBBAA - Sheet 01 Inspection of the NLG Aft Door Fwd Hinge Fwd Attachment Fitting

DATE: Feb 17/11 SERVICE BULLETIN No.: A340-52-5017 REVISION No.: 00 - Feb 17/11 Page: 42 5

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# @A340-500/600 SERVICE BULLETIN

**CONF ALL



### D 

## C

**D** F_SB_525017_5_BBAA_02_00 AREA TO BE INSPECTED TYPICAL CRACK

FORWARD ATTACHMENT FITTING Figure A-FBBAA - Sheet 02 Inspection of the NLG Aft Door Fwd Hinge Fwd Attachment Fitting

DATE: Feb 17/11 SERVICE BULLETIN No.: A340-52-5017 REVISION No.: 00 - Feb 17/11 Page: 43 5

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# @A340-500/600 SERVICE BULLETIN

**CONF ALL

Z715

Z716

LH SIDE SHOWN RH SIDE SYMMETRICAL 

### B **B**

**C** 

## B **A A**  Z120

F_SB_525017_5_BCAA_01_00 Figure A-FBCAA - Sheet 01 Inspection of the NLG Aft Door Fwd Hinge Fwd and Aft Attachment Fittings

DATE: Feb 17/11 SERVICE BULLETIN No.: A340-52-5017 REVISION No.: 00 - Feb 17/11 Page: 44 5

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# @A340-500/600 SERVICE BULLETIN

**CONF ALL



### D 

## C **E**

FWD ATTACHMENT FITTING

AFT ATTACHMENT FITTING 

## D

**E** AREA TO BE INSPECTED TYPICAL ADDITIONAL CRACKS

TYPICAL ADDITIONAL CRACK AREAS TO BE INSPECTED

F_SB_525017_5_BCAA_02_01 Figure A-FBCAA - Sheet 02 Inspection of the NLG Aft Door Fwd Hinge Fwd and Aft Attachment Fittings

DATE: Feb 17/11 SERVICE BULLETIN No.: A340-52-5017 REVISION No.: 00 - Feb 17/11 Page: 45 5

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# @A340-500/600 SERVICE BULLETIN

**CONF ALL

QUESTION ACTION FINDING CRACK FINDING NO

YES PERFORM HFEC INSPECTION AS PER NTM 51−10−08 PB6 OF THE NLG AFT DOOR FWD HINGE SWAN NECK IN

THE RADIUS & LUG AREA (LH & RH SIDE DOORS) REFER TO FIG. A−FBAAA AT THE THRESHOLD GIVEN IN PLANNING INFORMATION PARAGRAPH E.(2).

REPEAT EVERY 500 FC

REPLACE THE SWAN NECK AT FWD HINGE BY NEW ONE ON THE NLG AFT DOOR(S) WHERE THE FINDING(S)

HAVE BEEN IDENTIFIED BEFORE NEXT FLIGHT. REFER TO REPAIR PROCEDURE TASK 525017−833−801

SEND TO AIRBUS THE INSPECTION REPORT

F_SB_525017_5_BDAA_01_04 Figure A-FBDAA - Sheet 01 Flow Chart 1

DATE: Feb 17/11 SERVICE BULLETIN No.: A340-52-5017 REVISION No.: 00 - Feb 17/11 Page: 46 5

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# @A340-500/600 SERVICE BULLETIN

**CONF ALL

QUESTION ACTION FINDING CRACK YES NO

REPEAT EVERY 500 FC DO A DETAILED INSPECTION OF THE NLG AFT DOOR FWD

HINGE FWD ATTACHMENT FITTING (LH AND RH SIDES)

AND AFT ATTACHMENT FITTINGS ON THE NLG AFT DOOR(S) WHERE DO A HFEC INSPECTION OF THE FWD

CRACK FINDING YES NO FINDING

ADDITIONAL

REPLACE BOTH AFT AND FWD FITTINGS BY NEW ONES ON THE NLG AFT DOOR(S) WHERE THE FINDING(S) HAVE BEEN IDENTIFIED

SEND TO AIRBUS THE INSPECTION REPORT REFER TO FIGURE A−FBEAA SHEET 2 FROM FIGURE A−FBEAA SHEET 2 AT THE THRESHOLD GIVEN IN THE PLANNING INFORMATION PARAGRAPH E.(2).

REFER TO FIGURE A−FBBAA

THE FINDING(S) HAVE BEEN IDENTIFIED REFER TO FIGURE A−FBCAA REFER TO NTM 51−10−08 PB6

REFER TO REPAIR PROCEDURE TASK 525017−833−802

F_SB_525017_5_BEAA_01_04 Figure A-FBEAA - Sheet 01 Flow Chart 2

DATE: Feb 17/11 SERVICE BULLETIN No.: A340-52-5017 REVISION No.: 00 - Feb 17/11 Page: 47 5

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# @A340-500/600 SERVICE BULLETIN

**CONF ALL

QUESTION ACTION FINDING AND AFT ATTACHMENT FITTINGS ON THE NLG AFT DOOR(S) INSPECTION OF THE FWD WHERE THE FINDING(S)

CRACK FINDING YES NO ADDITIONAL

FINISHED YES NO 20 FC DO A PENETRANT AFT ATTACHMENT FITTINGS THE FWD AND

REFER TO FIGURE A−FBCAA REFER TO NTM 51−10−08 PB6 DO A HFEC INSPECTION OF

EVERY 10 FC OR WITHIN 20 FC FROM FIGURE A−FBEAA SHEET 1

REFER TO FIGURE A−FBEAA SHEET 1 HAVE BEEN IDENTIFIED REFER TO FIGURE A−FBCAA REFER TO NTM 51−80−00 PB1 EVERY 3 FC ON THE NLG AFT DOOR(S) WHERE THE FINDING(S) HAVE BEEN IDENTIFIED

F_SB_525017_5_BEAA_02_01 Figure A-FBEAA - Sheet 02 Flow Chart 2

DATE: Feb 17/11 SERVICE BULLETIN No.: A340-52-5017 REVISION No.: 00 - Feb 17/11 Page: 48 5

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# @A340-500/600 SERVICE BULLETIN

**CONF ALL

LH SIDE SHOWN RH SIDE SYMMETRICAL 

## ON BENCH

**A B** 

F_SB_525017_5_CBAA_01_00 Figure A-FCBAA - Sheet 01 Replacement of the NLG Aft Door Fwd Hinge Swan Neck

DATE: Feb 17/11 SERVICE BULLETIN No.: A340-52-5017 REVISION No.: 00 - Feb 17/11 Page: 49 5

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# @A340-500/600 SERVICE BULLETIN

**CONF ALL

**HOLE SYMBOL**  **ITEM PN**  **DESCRIPTION** NUT
NUT

WASHER WASHER

BOLT
BOLT

BOLT NUT ASNA2531−4 ASNA2027V4−9

ASNA2532−4
ASNA2397−10L

ASNA2531−4
ASNA2397−416L **MIN. MAX.**  **HOLE DIAMETER REMARKS**  6.390 mm (0.252 in)
5.100 mm (0.201 in) 5.000 mm (0.197 in)

6.390 mm (0.252 in) 6.440 mm (0.253 in) 6.440 mm (0.253 in) N

N

N (13)13

(13)13

18 (11) (14)14

(10)

(17) ASNA2027V3−8

ASNA2027V4−10 WET ASSEMBLY WITH MAT. No 09−013C 01 **NOTE:**

01
01

01 N HEAD ON VISIBLE SIDE 14 (18) (11)

(14) 

## A **A A** 

**A** 5 (5)



## A

(15) F_SB_525017_5_CBAA_02_03 Figure A-FCBAA - Sheet 02 Replacement of the NLG Aft Door Fwd Hinge Swan Neck

DATE: Feb 17/11 SERVICE BULLETIN No.: A340-52-5017 REVISION No.: 00 - Feb 17/11 Page: 50 5

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# @A340-500/600 SERVICE BULLETIN

**CONF ALL

APPLY MAT. No 09−016B 02 **NOTE:**
APPLY MAT. No 09−005−A 03 

### B

**B**



## B **B** 02 03 

## B

F_SB_525017_5_CBAA_03_02 Figure A-FCBAA - Sheet 03 Replacement of the NLG Aft Door Fwd Hinge Swan Neck

DATE: Feb 17/11 SERVICE BULLETIN No.: A340-52-5017 REVISION No.: 00 - Feb 17/11 Page: 51 5

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# @A340-500/600 SERVICE BULLETIN

**CONF ALL

LH SIDE SHOWN RH SIDE SYMMETRICAL

F_SB_525017_5_CAAA_01_00 

## ON BENCH

**A B** 

Figure A-FCAAA - Sheet 01 Replacement of the NLG Aft Door Fwd Hinge Fwd and Aft Attachment Fittings

DATE: Feb 17/11 SERVICE BULLETIN No.: A340-52-5017 REVISION No.: 00 - Feb 17/11 Page: 52 5

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# @A340-500/600 SERVICE BULLETIN

**CONF ALL

**HOLE SYMBOL**  **ITEM PN**  **DESCRIPTION** NUT

WASHER

BOLT

BOLT NUT ASNA2531−4 ASNA2027V4−9

ASNA2531−4
ASNA2397−416L **MIN. MAX.**  **HOLE DIAMETER REMARKS**  6.390 mm (0.252 in)

6.390 mm (0.252 in) 6.440 mm (0.253 in) 6.440 mm (0.253 in) N

N (13)13

(13)13

(10)

(17) ASNA2027V4−10 02

02 

## A

NUT BOLT ASNA2532−4 ASNA2001T4−28 6.339 mm (0.250 in) 6.375 mm (0.251 in) F (14)14 (11) F N HEAD ON HIDDEN SIDE HEAD ON VISIBLE SIDE APPLY MAT. No 08−078 01 **NOTE:** WET ASSEMBLY WITH MAT. No 09−013C 02 TORQUE VALUE BETWEEN 0.7 AND 0.9 m.daN (62 AND 80 lbf.in) 03 2 4 (2) (4) LH RH

LH RH (1) (3) 1 3

02 03

(15) 

## C **C**

01

F_SB_525017_5_CAAA_02_04 Figure A-FCAAA - Sheet 02 Replacement of the NLG Aft Door Fwd Hinge Fwd and Aft Attachment Fittings

DATE: Feb 17/11 SERVICE BULLETIN No.: A340-52-5017 REVISION No.: 00 - Feb 17/11 Page: 53 5

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# @A340-500/600 SERVICE BULLETIN

**CONF ALL

APPLY MAT. No 09−016B 02 **NOTE:** APPLY MAT. No 09−005−A 03 02 03

APPLY MAT. No 16−021 04 04 02 04 02 

## B

**A A**  **A A** 

F_SB_525017_5_CAAA_03_02 Figure A-FCAAA - Sheet 03 Replacement of the NLG Aft Door Fwd Hinge Fwd and Aft Attachment Fittings

DATE: Feb 17/11 SERVICE BULLETIN No.: A340-52-5017 REVISION No.: 00 - Feb 17/11 Page: 54 5

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# @A340-500/600 SERVICE BULLETIN

**CONF ALL

**ELAPSED TIME ASSUMPTIONS SERVICE BULLETIN No. A340−52−5017**

ELAPSED TIME (HOURS)

**NOTE:** THIS CHART IS ONLY A PROPOSAL. OPERATORS MAY DETERMINE THAT ANOTHER WAY TO DO THE WORK IS MORE SUITABLE FOR THEM. MH ET PER

MH: ET: PER: MANHOURS ELAPSED TIME NUMBER OF PERSONS

TOTAL MANHOURS (MH) ELAPSED TIME (ET) 5.00 5.00 STEPS

0 GET ACCESS 1.00 1.00 1

CLOSE−UP 1.00 1.00 1 DO AN INSPECTION OF THE NLG AFT DOOR FWD HINGE (LH AND RH SIDE)

1 2345 3.00 3.00 1

F_SB_525017_5_ACAA_01_00 Figure A-FACAA - Sheet 01 Elapsed Time Assumptions For NLG Aft Door Fwd Hinge Inspection

DATE: Feb 17/11 SERVICE BULLETIN No.: A340-52-5017 REVISION No.: 00 - Feb 17/11 Page: 55 5

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# @A340-500/600 SERVICE BULLETIN

**CONF ALL

**ELAPSED TIME ASSUMPTIONS SERVICE BULLETIN No. A340−52−5017**

ELAPSED TIME (HOURS)

**NOTE:** THIS CHART IS ONLY A PROPOSAL. OPERATORS MAY DETERMINE THAT ANOTHER WAY TO DO THE WORK IS MORE SUITABLE FOR THEM. MH ET PER

MH: ET: PER: MANHOURS ELAPSED TIME NUMBER OF PERSONS

TOTAL MANHOURS (MH) ELAPSED TIME (ET) 13.00 13.00 STEPS

0 GET ACCESS 3.00 3.00 1

CLOSE−UP 6.00 6.00 1 REPLACE THE NLG AFT DOOR FWD HINGE SWAN NECK OF THE LH DOOR

1 2 13 2.00 2.00 1

2.00 2.00 1

3 4 5 6 7 8 9 12 11 10 REPLACE THE NLG AFT DOOR FWD HINGE SWAN NECK OF THE RH DOOR

F_SB_525017_5_ADAA_01_00 Figure A-FADAA - Sheet 01 Elapsed Time Assumptions For replacement of the NLG Aft Door Fwd Hinge Swan Neck

DATE: Feb 17/11 SERVICE BULLETIN No.: A340-52-5017 REVISION No.: 00 - Feb 17/11 Page: 56 5

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# @A340-500/600 SERVICE BULLETIN

**CONF ALL

**ELAPSED TIME ASSUMPTIONS SERVICE BULLETIN No. A340−52−5017**

ELAPSED TIME (HOURS)

**NOTE:** THIS CHART IS ONLY A PROPOSAL. OPERATORS MAY DETERMINE THAT ANOTHER WAY TO DO THE WORK IS MORE SUITABLE FOR THEM. MH ET PER

MH: ET: PER: MANHOURS ELAPSED TIME NUMBER OF PERSONS

TOTAL MANHOURS (MH) ELAPSED TIME (ET) 21.00 21.00 STEPS

0 GET ACCESS 3.00 3.00 1

CLOSE−UP 6.00 6.00 1 REPLACE THE NLG AFT DOOR FWD HINGE FITTING OF THE LH DOOR

3 21 6.00 6.00 1

6.00 6.00 1 REPLACE THE NLG AFT DOOR FWD HINGE FITTING OF THE RH DOOR

6 9 18 15 12

F_SB_525017_5_AEAA_01_00 Figure A-FAEAA - Sheet 01 Elapsed Time Assumptions For replacement of the NLG Aft Door Fwd Hinge Fittings

DATE: Feb 17/11 SERVICE BULLETIN No.: A340-52-5017 REVISION No.: 00 - Feb 17/11 Page: 57 5

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# @A340-500/600 SERVICE BULLETIN

This Page Intentionally Left Blank

DATE: Feb 17/11 SERVICE BULLETIN No.: A340-52-5017 REVISION No.: 00 - Feb 17/11 Page: 58 5

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# @A340-500/600 SERVICE BULLETIN Appendix 1 **CONF ALL (1) Inspection Report The results of the inspection, including no findings, replacement or actions to be done, must be forwarded to AIRBUS Department SEES3, on the attached inspection report sheet. NOTE: Indicate on the report sheet the location and max sizes of the crack.

DATE: Feb 17/11 SERVICE BULLETIN No.: A340-52-5017 REVISION No.: 00 - Feb 17/11 Page: 1 5

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# @A340-500/600 SERVICE BULLETIN Appendix 1
**CONF ALL

FWD FITTING AFT FITTING LH SIDE RH SIDE LH SIDE RH SIDE NO CRACK

CRACK ADDITIONAL CRACK FWD ATTACHMENT FITTING

AFT ATTACHMENT FITTING

F_SB_525017_5_AAAA_01_03 **INSPECTION REPORT** SERVICE BULLETIN No. : A/C MSN : FLIGHT CYCLES : FLIGHT HOURS : A340−52−5017

DATE OF INSPECTION : RETURN TO : AIRBUS CUSTOMER SERVICES ENGINEERING − SEES3 DOORS − HORIZONTAL TAIL PLANE −

INSPECTION METHOD : 1 ROND POINT MAURICE BELLONTE 31707 BLAGNAC CEDEX FRANCE FAX +33 (0)5 61 93 36 14 AIRCRAT RECOVERY MANUAL DETAILED INSPECTION HFEC INSPECTION HF EDDY CURRENT INSPECTION WING MOVEABLE SURFACES −

Figure A-FAAAA - Sheet 01

Fitting Inspection Report

DATE: Feb 17/11 SERVICE BULLETIN No.: A340-52-5017 REVISION No.: 00 - Feb 17/11 Page: 2 5

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# @A340-500/600 SERVICE BULLETIN Appendix 2 **CONF ALL (1) Inspection Report The results of the inspection, including no findings, replacement or actions to be done, must be forwarded to AIRBUS Department SEES3, on the attached inspection report sheet. NOTE: Indicate on the report sheet the location and max sizes of the crack.

DATE: Feb 17/11 SERVICE BULLETIN No.: A340-52-5017 REVISION No.: 00 - Feb 17/11 Page: 1 5

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# @A340-500/600 SERVICE BULLETIN Appendix 2
**CONF ALL

HINGE No 4 SWAN NECK LH SIDE RH SIDE NO CRACK

CRACK HINGE No 4 SWAN NECK

F_SB_525017_5_ABAA_01_03 **INSPECTION REPORT** SERVICE BULLETIN No. : A/C MSN : FLIGHT CYCLES : FLIGHT HOURS : A340−52−5017

DATE OF INSPECTION : RETURN TO : AIRBUS CUSTOMER SERVICES ENGINEERING − SEES3 DOORS − HORIZONTAL TAIL PLANE −

INSPECTION METHOD : 1 ROND POINT MAURICE BELLONTE 31707 BLAGNAC CEDEX FRANCE FAX +33 (0)5 61 93 36 14 AIRCRAT RECOVERY MANUAL HFEC INSPECTION WING MOVEABLE SURFACES −

Figure A-FABAA - Sheet 01 Swan Neck Inspection Report

DATE: Feb 17/11 SERVICE BULLETIN No.: A340-52-5017 REVISION No.: 00 - Feb 17/11 Page: 2 5

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# @A340-500/600 SERVICE BULLETIN REPORTING SHEET 

### TITLE: DOORS - NLG AFT DOORS - INSPECTION FOR CRACKS ON FWD HINGE FITTINGS MODIFICATION No.: None Please complete the appropriate item (A or B): A - SB WILL BE embodied YES/NO (if NO please comment) If YES, aircraft concerned (as per SB effectivity by default) and planned dates (month/year) of embodiment:

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

DATE: Feb 17/11 SERVICE BULLETIN No.: A340-52-5017 REVISION No.: 00 - Feb 17/11 Page: 1 5

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# @A340-500/600 SERVICE BULLETIN QUALITY PERCEPTION FORM Use this form to tell us what is your perception of the quality of this Service Bulletin. The reported data that you provide us will be used to analyse areas of difficulties and to take corrective action to further improve the quality of our Service Bulletins. We thank you for the time you have taken in completing this form. (Please rate on a scale of 1 to 4, with 4 being the highest score) - Quality rating of this SB 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: Feb 17/11 SERVICE BULLETIN No.: A340-52-5017 REVISION No.: 00 - Feb 17/11 Page: 1 5

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