@A340-500/600

SERVICE BULLETIN

SUMMARY

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX

FRANCE

Tel : (33) 5 61 93 33 33

Telex : AIRBU 530526F

Fax : (33) 5 61 93 42 51

This summary is for information only and is not approved for modification of the aircraft.

MANDATORY MANDATORY MANDATORY

ATA SYSTEM: 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

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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

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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

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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

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Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340-500/600

SERVICE BULLETIN

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX

FRANCE

Tel : (33) 5 61 93 33 33

Telex : AIRBU 530526F

Fax : (33) 5 61 93 42 51

MANDATORY MANDATORY MANDATORY

ATA SYSTEM: 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

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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

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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

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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

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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

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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 per

Fig. 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 per

Fig. 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 per

Fig. 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

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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. EASA 21J.031.

If an aircraft listed in the effectivity has a modification or repair embodied that is not of

AIRBUS origin, and which affects the content of this Service Bulletin, the operator is

responsible for obtaining approval by its airworthiness authority for any adaptation necessary

before incorporation of the Service Bulletin.

G. MANPOWER

The manpower estimates given in this Service Bulletin are based on the direct labor cost to

do the work. These estimates assume that the work will be done by experienced personnel,

and may need to be revised upwards to suit operator’s circumstances. The estimates do not

include the time to prepare, plan or inspect the work. Manufacture and procurement of parts

and tools, drying times for paints, sealants, etc., and general administration work are also not

included.

Task 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

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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

DATE: Feb 17/11 SERVICE BULLETIN No.: A340-52-5017

REVISION No.: 00 - Feb 17/11 Page: 8

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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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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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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

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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)

DATE: Feb 17/11 SERVICE BULLETIN No.: A340-52-5017

REVISION No.: 00 - Feb 17/11 Page: 31

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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

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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

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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

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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

DATE: Feb 17/11 SERVICE BULLETIN No.: A340-52-5017

REVISION No.: 00 - Feb 17/11 Page: 35

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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

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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

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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

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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

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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

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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

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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

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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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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

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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

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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

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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

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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

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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

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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

N (0.253 in)

N

N

(13)13

(13)13

18

(11)

(14)14

(10)

(17)

ASNA2027V3−8

ASNA2027V4−10

01 WET ASSEMBLY WITH MAT. No 09−013C

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

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SERVICE BULLETIN

**CONF ALL

02 APPLY MAT. No 09−016B

NOTE:

03 APPLY MAT. No 09−005−A

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

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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

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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

N (0.253 in)

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

01 APPLY MAT. No 08−078

NOTE:

02 WET ASSEMBLY WITH MAT. No 09−013C

03 TORQUE VALUE BETWEEN 0.7 AND 0.9 m.daN (62 AND 80 lbf.in)

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

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SERVICE BULLETIN

**CONF ALL

02 APPLY MAT. No 09−016B

NOTE:

03 APPLY MAT. No 09−005−A

02

03

04 APPLY MAT. No 16−021

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

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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

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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 10 11 12

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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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 12 15 18

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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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

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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

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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

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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

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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

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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

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