@A340-500/600

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX

FRANCE

Tel : (33) 5 61 93 33 33

Telex : AIRBU 530526F

Fax : (33) 5 61 93 42 51

MANDATORY MANDATORY MANDATORY

ATA SYSTEM: 34

TITLE: NAVIGATION - GENERAL - REPLACE AOA PROBE CONIC PLATE BY

AOA PROBE FLAT PLATE

MODIFICATION No.: 203295S32646

This page transmits Revision No.01 of Service Bulletin No.A340-34-5093

ADDITIONAL WORK

**CONF ALL

Additional work is required by this revision for aircraft modified by any previous issue.

REASON

Revision No. 01 issued to modify the installation of the two AOA cover plates on RH side in order to

ensure that both plates are flush with the fuselage (Refer to SBIT No. 13-0017), and to apply minor

changes.

CHANGES

SUMMARY

MATERIAL PRICE INFORMATION MATERIAL PRICE INFORMATION TABLE

UPDATED

R

MATERIAL PRICE INFORMATION TABLE

UPDATED

R

EFFECTIVITY OPERATOR LIST UPDATED R

REFERENCES / REPERCUSSIONS REFERENCES/REPERCUSSIONS TABLE

UPDATED

R

MANPOWER MANPOWER UPDATED R

MANPOWER UPDATED R

Fig. A-FSAAA FIGURE SOLUTION UPDATED R

Fig. A-FSAAA Sheet 01 SHEET UPDATED R

Fig. A-FSAAA Sheet 02 SHEET UPDATED R

Fig. A-FSAAA Sheet 03 SHEET ADDED N

DATE: Jan 30/13 SERVICE BULLETIN No.: A340-34-5093

REVISION No.: 01 - Jun 12/13 Page: 1

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REVISION TRANSMITTAL SHEET

PLANNING INFORMATION

EFFECTIVITY EFFECTIVITY RELATED INFORMATION

UPDATED

R

Material Effectivity MATERIAL EFFECTIVITY UPDATED

MATERIAL SET QUANTITY UPDATED

MATERIAL SET UPDATED

R

COMPLIANCE

Accomplishment Timescale ACCOMPLISHMENT TIMESCALE UPDATED R

APPROVAL APPROVAL UPDATED R

MANPOWER MANPOWER UPDATED R

MANPOWER UPDATED R

MATERIAL INFORMATION

MATERIAL - PRICE AND AVAILABILITY

Procurement Addresses PROCUREMENT ADDRESSES UPDATED

MATERIAL SET UPDATED

R

Price and Availability PRICE AND AVAILABILITY UPDATED

MATERIAL SET UPDATED

R

INDUSTRY SUPPORT INFORMATION INDUSTRY SUPPORT INFORMATION UPDATED R

LIST OF MATERIALS - OPERATOR

SUPPLIED

Consumable Materials

Consumable CMLA01 CONSUMABLE MATERIAL SET UPDATED

CONSUMABLE UPDATED

R

Components COMPONENTS UPDATED R

Component COMPA02 PART MATERIAL SET UPDATED

QUANTITY UPDATED

ITEM NUMBER UPDATED

PART NUMBER UPDATED

KEYWORD UPDATED

R

Component COMPA03 PART MATERIAL SET ADDED N

ACCOMPLISHMENT INSTRUCTIONS

TASK 345093- 831-801-001-Modification

of the AOA sensor plates.

Subtask 345093-941-004-001 SUBTASK SOLUTION ADDED N

Subtask 345093-941-001-001 SUBTASK SOLUTION DELETED FOR

APPLICABLE MSN

D

Subtask 345093-941-004-002 SUBTASK SOLUTION ADDED N

Subtask 345093-941-001-002 SUBTASK SOLUTION DELETED FOR

APPLICABLE MSN

D

Subtask 345093-831-001-001 SUBTASK SOLUTION UPDATED

CONSUMABLE UPDATED

REFERENCED DOCUMENTATION UPDATED

MATERIAL LIST UPDATED

REFERENCES UPDATED

R

DATE: Jan 30/13 SERVICE BULLETIN No.: A340-34-5093

REVISION No.: 01 - Jun 12/13 Page: 2

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REVISION TRANSMITTAL SHEET

Subtask 345093-831-002-001 SUBTASK SOLUTION UPDATED

QUANTITY UPDATED

ITEM NUMBER UPDATED

PART NUMBER UPDATED

KEYWORD UPDATED

CONSUMABLE UPDATED

REFERENCED DOCUMENTATION UPDATED

FIGURE REFERENCE UPDATED

CONFIGURATION UPDATED

PART NUMBER DESCRIPTION UPDATED

MATERIAL LIST UPDATED

REFERENCES UPDATED

NOTE UPDATED

R

Subtask 345093-831-001-001 SUBTASK SOLUTION UPDATED

CONSUMABLE UPDATED

REFERENCED DOCUMENTATION UPDATED

MATERIAL LIST UPDATED

REFERENCES UPDATED

R

Subtask 345093-831-002-001 SUBTASK SOLUTION UPDATED

QUANTITY UPDATED

ITEM NUMBER UPDATED

PART NUMBER UPDATED

KEYWORD UPDATED

CONSUMABLE UPDATED

REFERENCED DOCUMENTATION UPDATED

FIGURE REFERENCE UPDATED

CONFIGURATION UPDATED

PART NUMBER DESCRIPTION UPDATED

MATERIAL LIST UPDATED

REFERENCES UPDATED

NOTE UPDATED

R

Subtask 345093-700-001-001 SUBTASK SOLUTION UPDATED

NOTE UPDATED

REFERENCED DOCUMENTATION UPDATED

R

Subtask 345093-700-001-001 SUBTASK SOLUTION UPDATED

NOTE UPDATED

REFERENCED DOCUMENTATION UPDATED

R

Subtask 345093-942-001-001 SUBTASK SOLUTION UPDATED

CONSUMABLE UPDATED

CONFIGURATION UPDATED

FIGURE REFERENCE UPDATED

MATERIAL LIST UPDATED

REFERENCES UPDATED

R

Subtask 345093-942-001-002 SUBTASK SOLUTION UPDATED

CONSUMABLE UPDATED

CONFIGURATION UPDATED

FIGURE REFERENCE UPDATED

MATERIAL LIST UPDATED

REFERENCES UPDATED

R

TASK 345093- 831-802-001-Additional

Work

TASK SOLUTION ADDED N

DATE: Jan 30/13 SERVICE BULLETIN No.: A340-34-5093

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REVISION TRANSMITTAL SHEET

Task associated data - 001 TASK ASSOCIATED DATA ADDED N

Task associated data - 002 TASK ASSOCIATED DATA ADDED N

Subtask 345093-910-002-001 SUBTASK SOLUTION ADDED N

Subtask 345093-839-002-001 SUBTASK SOLUTION ADDED N

Subtask 345093-910-002-001 SUBTASK SOLUTION ADDED N

Subtask 345093-839-002-001 SUBTASK SOLUTION ADDED N

Subtask 345093-941-002-001 SUBTASK SOLUTION ADDED N

Subtask 345093-941-002-001 SUBTASK SOLUTION ADDED N

Subtask 345093-831-004-001 SUBTASK SOLUTION ADDED N

Subtask 345093-831-004-001 SUBTASK SOLUTION ADDED N

Subtask 345093-700-002-001 SUBTASK SOLUTION ADDED N

Subtask 345093-700-002-001 SUBTASK SOLUTION ADDED N

Subtask 345093-942-002-001 SUBTASK SOLUTION ADDED N

Subtask 345093-942-002-001 SUBTASK SOLUTION ADDED N

Fig. A-FBAAA FIGURE SOLUTION UPDATED R

Fig. A-FBAAA Sheet 01 SHEET UPDATED R

Fig. A-FBAAA Sheet 02 SHEET UPDATED R

Fig. A-FBCAA FIGURE SOLUTION ADDED N

Fig. A-FBCAA Sheet 01 SHEET ADDED N

Fig. A-FBCAA Sheet 02 SHEET ADDED N

Fig. A-FBDAA FIGURE SOLUTION ADDED N

Fig. A-FBDAA Sheet 01 SHEET ADDED N

Fig. A-FBDAA Sheet 02 SHEET ADDED N

FILLING INSTRUCTIONS

This Service Bulletin has been generated electronically and is reissued as a complete document.

Replace the complete document.

Put this Revision Transmittal Sheet in front of the Service Bulletin.

HISTORY OF PREVIOUS REVISIONS

No previous revision

REVISION SEQUENCE

ORIGINAL: Jan 30/13

REVISION No. : 01 - Jun 12/13

DATE: Jan 30/13 SERVICE BULLETIN No.: A340-34-5093

REVISION No.: 01 - Jun 12/13 Page: 4

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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: 34

TITLE: NAVIGATION - GENERAL - REPLACE AOA PROBE CONIC PLATE BY

AOA PROBE FLAT PLATE

**CONF ALL

MODIFICATIONS

MODIFICATION CLASSIFICATION

MAJOR 203295S32646

MINOR None

NOTE: As per EASA IR 21, a minor change is one that has no appreciable effect on the

mass, balance, structural strength, reliability, operational characteristics affecting the

airworthiness of the product. All other changes are major changes.

REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

Following a recent in-service event, as a precautionary measure, Airbus requires to suspend the

installation of the AOA (Angle Of Attack) conic plates as per Operator Information Transmission (OIT)

No. 999.0086/12, currently performed through an Airbus monitored campaign with Service Bulletin No.

A340-34-5081.

This modification requires the removal of the conic plates PN F3411060200000 and PN

F3411060900000, and the installation of flat plates PN F3411007920200 (LH) / PN F3411007920300

(RH).

Also, it requires to change the 3 AOA Sensor Protection Covers (FINs 7955ME, 7956ME and 7957ME)

stored in Flight Kit No 2 (FIN 7500NW or FIN 7503NW).

Refer to OIT No. 999.0086/12 and FOT No. 999.0089/12 for further explanations.

For aircraft already fitted with the AOA conic plates through retrofit or from production, Airbus released

associated operational recommendations in an FOT No. 999.0089/12, the Operations Engineering

Bulletin (OEB) 45 and Flight Manual (FM) Temporary Revision 294.

This Service Bulletin modifies the Ground System Equipment (the AOA Protection Covers) needed for

parking, mooring or storing the aircraft.

DATE: Jan 30/13 SERVICE BULLETIN No.: A340-34-5093

REVISION No.: 01 - Jun 12/13 Page: 1

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SUMMARY

Accomplishment of this Service Bulletin cancels OEB 45 and FM TR294. It is expected that an

Airworthiness Directive (AD) published by the European Aviation Safety Agency (EASA) will be issued

to confirm this cancellation.

This Service Bulletin modifies the Ground System Equipment (the AOA Protection Covers) needed for

parking, mooring or storing the aircraft.

The operational consequence of this Service Bulletin is the modification of the Flight Manual (FM) and

Flight Crew Operating Manual (FCOM) by removing temporary operational measures introduced by

OEB 45, FOT No. 999.0089/12 and FM TR294.

GENERAL EVALUATION

EVALUATION TABLE

COMPLIANCE MANDATORY (1) CANCELS INSPECTION SB NO

POTENTIAL AD YES A/C OPERATION AFFECTED YES

RELIABILITY AFFECTED NO PAX COMFORT AFFECTED NO

COST SAVING NO LROPS AFFECTED NO

STRUCTURAL LIFE EXTN NO VENDOR SB INVOLVED NO

NOTE (1): Service Bulletin must be accomplished.

MATERIAL PRICE INFORMATION

**CONF 001

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Component COMPA01 1 See SB Flat Plates, Covers

Component COMPA02 1 See SB Screws

Component COMPA03 1 See SB Screws

**CONF 002

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Component COMPA01 1 See SB Flat Plates, Covers

Component COMPA02 1 See SB Screws

Component COMPA03 1 See SB Screws

EFFECTIVITY

**CONF ALL

This Service Bulletin is applicable to this (these) operator(s) :

06U 25R 36V 70U 72W AHY CES CHH DLH ETD HFY IBE QAF

QTR SAA SIA TAM THA UAE VIR

DATE: Jan 30/13 SERVICE BULLETIN No.: A340-34-5093

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SERVICE BULLETIN

SUMMARY

CONCURRENT REQUIREMENTS

None

REFERENCES / REPERCUSSIONS

TFU None

OEB 45

AOT None

SIL None

LINE MAINTENANCE AFFECTED No

LIFE LIMIT None

OTHER OIT No. 999.0086/12

OTHER FOT No. 999.0089/12

OTHERS SBIT No. 13-0017

NATURE OF THE WORK

AIRCRAFT YES

EQUIPMENT NO

HARD NO

SOFT NO

OBRM NO

MANPOWER

**CONF 001

Task 345093-831-801-001: Modification of the AOA sensor plates.

TOTAL MANHOURS 6.25

ELAPSED TIME (HOURS) 4.25

Task 345093-831-802-001: Additional Work

TOTAL MANHOURS 4.25

ELAPSED TIME (HOURS) 4.25

**CONF 002

Task 345093-831-801-001: Modification of the AOA sensor plates.

TOTAL MANHOURS 6.25

ELAPSED TIME (HOURS) 4.25

Task 345093-831-802-001: Additional Work

TOTAL MANHOURS 4.25

ELAPSED TIME (HOURS) 4.25

DATE: Jan 30/13 SERVICE BULLETIN No.: A340-34-5093

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SERVICE BULLETIN

SUMMARY

APPENDICES

**CONF ALL

APPENDIX 01: Elapsed Time Assumption

DATE: Jan 30/13 SERVICE BULLETIN No.: A340-34-5093

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SUMMARY

**CONF ALL

NOTE:

TYPICAL ILLUSTRATION ASSOCIATED WITH THALES OR GOODRICH AOA SENSORS.

BEFORE

FR19

FR18

3FP1

3FP2

3FP3

A

A

A

OR

THALES GOODRICH

C

C

A B

F_SB_345093_5_SAAA_01_02

Figure A-FSAAA - Sheet 01

DATE: Jan 30/13 SERVICE BULLETIN No.: A340-34-5093

REVISION No.: 01 - Jun 12/13 Page: 5

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SUMMARY

**CONF ALL

TYPICAL ILLUSTRATION ASSOCIATED WITH THALES OR GOODRICH AOA SENSORS.

AFTER

CAUTION:

NEW AOA FLAT PLATES SHALL NOT BE PAINTED AND SHALL REMAIN AS DELIVERED.

NOTE:

DEPENDS ON AIRCRAFT CONFIGURATION.

ONLY ONE CONFIGURATION LH SIDE SHOWN, AOA SENSOR

B

FWD

F_SB_345093_5_SAAA_02_02

Figure A-FSAAA - Sheet 02

DATE: Jan 30/13 SERVICE BULLETIN No.: A340-34-5093

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SUMMARY

**CONF ALL

TYPICAL ILLUSTRATION ASSOCIATED WITH THALES OR GOODRICH AOA SENSORS.

AFTER

CAUTION:

NEW AOA FLAT PLATES SHALL NOT BE PAINTED AND SHALL REMAIN AS DELIVERED.

C

NOTE:

DEPENDS ON AIRCRAFT CONFIGURATION.

ONLY ONE CONFIGURATION RH SIDE SHOWN, AOA SENSOR

FWD

F_SB_345093_5_SAAA_03_00

Figure A-FSAAA - Sheet 03

DATE: Jan 30/13 SERVICE BULLETIN No.: A340-34-5093

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SUMMARY

**CONF 001

B

FR69

FR73

A

A

Z160

B

7500NW

FLIGHT KIT No 2

NOTE:

ARE STORED IN FLIGHT KIT No 2 FIN (7500NW)

AOA PROTECTION COVERS FINs (7955ME, 7956ME AND 7957ME)

F_SB_345093_5_SBAA_01_01

Figure A-FSBAA - Sheet 01

DATE: Jan 30/13 SERVICE BULLETIN No.: A340-34-5093

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SERVICE BULLETIN

SUMMARY

**CONF 002

A

A

Z130

FR20

FR25

FR26

B

FLIGHT KIT No 2

NOTE:

ARE STORED IN FLIGHT KIT No 2 FIN (7503NW)

AOA PROTECTION COVERS FINs (7955ME, 7956ME AND 7957ME)

B

7503NW

F_SB_345093_5_SBAB_01_01

Figure A-FSBAB - Sheet 01

DATE: Jan 30/13 SERVICE BULLETIN No.: A340-34-5093

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SUMMARY

This Page Intentionally Left Blank

DATE: Jan 30/13 SERVICE BULLETIN No.: A340-34-5093

REVISION No.: 01 - Jun 12/13 Page: 10

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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: 34

TITLE: NAVIGATION - GENERAL - REPLACE AOA PROBE CONIC PLATE BY

AOA PROBE FLAT PLATE

MODIFICATION No.: 203295S32646

This document contains AIRBUS PROPRIETARY INFORMATION and shall at all times remain the

property of AIRBUS; no intellectual property right or licence is granted by AIRBUS in connection with

any information contained in it. It is delivered on the express condition that said document and the

information contained in it shall be treated as confidential, shall not be used for any purpose other than

that for which it is hereby delivered. It shall not be disclosed in whole or in part to third parties and shall

not be duplicated in any manner (except for the purposes of performing the tasks described hereunder

and provided that any recipient of such document shall comply with the conditions herein), without

AIRBUS prior written consent.

1. PLANNING INFORMATION

**CONF ALL

A. EFFECTIVITY

NOTE: This modification is applicable by Service Bulletin only.

NOTE: This Service Bulletin is only applicable to aircraft listed below on which Mod.

No. 201609S31961 (INSTALL A NEW CONIC PLATE FOR NEW AOA

(ANGLE OF ATTACK SENSOR) THALES) or Mod. No. 201610S31887

(INSTALL A NEW CONIC PLATE FOR NEW AOA (ANGLE OF ATTACK

SENSOR) GOODRICH AND OLD THALES) are embodied or on which

Service Bulletin No. A340-34-5081 is accomplished.

(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

DATE: Jan 30/13 SERVICE BULLETIN No.: A340-34-5093

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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

(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

25R 0924

36V 0391 0416

70U 0902

72W 0917

AHY 0779 0886 0894

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

HFY 0910 0912

IBE 0431 0440 0460 0601 0604 0606 0617 0619 0672 0702 0727 0744

0960 0993 1017 1079 1122

QAF 0495

QTR 0715 0740 0766 0798

SAA 0410 0417 0426 0531 0534 0547 0557 0626 0630

SIA 0478 0492 0499 0560 0563

TAM 0445 0464

THA 0624 0628 0677 0681 0689 0698 0710 0719 0775 0953

UAE 0394 0457 0471 0485 0520 0572 0608 0611 0685 0694

VIR 0371 0376 0383 0449 0575 0615 0622 0639 0706 0723 0736 0753

0764 0765 0768 0787 0804

(4) Configuration by MSN

MSN CONFIGURATION

0371 0376 0383 0391 0416 0449 001

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MSN CONFIGURATION

0394 0410 0417 0426 0431 0436 0440 0445 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

002

(5) Configuration definition

**CONF 001

Config. 001 is valid for aircraft on which Mod. No. 50648D44169 is not embodied.

**CONF 002

Config. 002 is valid for aircraft on which Mod. No. 50648D44169 is embodied.

(6) Material Effectivity

MATERIAL QTY PER A/C SEE NOTES

Consumable CMLA01 1

Component COMPA01 1

Component COMPA02 1

Component COMPA03 1

B. CONCURRENT REQUIREMENTS

None

C. REASON

(1) History

Following a recent in-service event, as a precautionary measure, Airbus requires to

suspend the installation of the AOA (Angle Of Attack) conic plates as per Operator

Information Transmission (OIT) No. 999.0086/12, currently performed through an Airbus

monitored campaign with Service Bulletin No. A340-34-5081.

(2) Objective/Action

This modification requires the removal of the conic plates PN F3411060200000 and PN

F3411060900000, and the installation of flat plates PN F3411007920200 (LH) / PN

F3411007920300 (RH).

Also, it requires to change the 3 AOA Sensor Protection Covers (FINs 7955ME, 7956ME

and 7957ME) stored in Flight Kit No 2 (FIN 7500NW or FIN 7503NW).

DATE: Jan 30/13 SERVICE BULLETIN No.: A340-34-5093

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(3) Advantages

Refer to OIT No. 999.0086/12 and FOT No. 999.0089/12 for further explanations.

(4) Operational/Maintenance Consequences

For aircraft already fitted with the AOA conic plates through retrofit or from production,

Airbus released associated operational recommendations in an FOT No. 999.0089/12,

the Operations Engineering Bulletin (OEB) 45 and Flight Manual (FM) Temporary

Revision 294.

This Service Bulletin modifies the Ground System Equipment (the AOA Protection

Covers) needed for parking, mooring or storing the aircraft.

Accomplishment of this Service Bulletin cancels OEB 45 and FM TR294. It is expected

that an Airworthiness Directive (AD) published by the European Aviation Safety Agency

(EASA) will be issued to confirm this cancellation.

This Service Bulletin modifies the Ground System Equipment (the AOA Protection

Covers) needed for parking, mooring or storing the aircraft.

The operational consequence of this Service Bulletin is the modification of the Flight

Manual (FM) and Flight Crew Operating Manual (FCOM) by removing temporary

operational measures introduced by OEB 45, FOT No. 999.0089/12 and FM TR294.

D. DESCRIPTION

To accomplish this Service Bulletin it is necessary to :

**CONF 001

Task 345093-831-801-001: Modification of the AOA sensor plates.

(1) Replace the Conic Plate of the AOA Sensor FIN 3FP1, on the LH Side.

(2) Replace the Conic Plates of the AOA Sensors FINs 3FP2 and 3FP3, on the RH

Side.

(3) Replace the AOA Protection Covers in the Flight Kit No 2 (FIN 7500NW).

Task 345093-831-802-001: Additional Work

(1) Modify the flat Plates position at level of the AOA Sensors FINs 3FP2 and 3FP3, on

the RH side

**CONF 002

Task 345093-831-801-001: Modification of the AOA sensor plates.

(1) Replace the Conic Plate of the AOA Sensor FIN 3FP1, on the LH Side.

(2) Replace the Conic Plates of the AOA Sensors FINs 3FP2 and 3FP3, on the RH

Side.

DATE: Jan 30/13 SERVICE BULLETIN No.: A340-34-5093

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(3) Replace the AOA Protection Covers in the Flight Kit No 2 (FIN 7503NW).

Task 345093-831-802-001: Additional Work

(1) Modify the flat Plates position at level of the AOA Sensors FINs 3FP2 and 3FP3, on

the RH side

**CONF ALL

E. COMPLIANCE

(1) Classification

MANDATORY: Service Bulletin must be accomplished.

(2) Accomplishment Timescale

This Service Bulletin has been classified Mandatory by the issue of an Airworthiness

Directive (AD) published by the European Aviation Safety Agency (EASA). The AD must

be used as the reference document for the mandated accomplishment timescale.

Table 1: Modification of the AOA sensor plates

Condition Action Compliance Time

Threshold Grace Period

Config. 001 First application 5 months after AD

effective date

None

Table 2: Additional Work

Condition Action Compliance Time

Threshold Grace Period

For aircraft on which

this SB at its initial issue

is accomplished

Accomplishment of

Additional Work

At next C-check at the

latest

None

F. APPROVAL

The technical content of this document is approved under the authority of Design

Organization Approval No. EASA.21J.031.

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

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

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

before incorporation of the Service Bulletin.

G. MANPOWER

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

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

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

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

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

included.

DATE: Jan 30/13 SERVICE BULLETIN No.: A340-34-5093

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**CONF 001

Task 345093-831-801-001: Modification of the AOA sensor plates.

Get Access 0.50

On Aircraft

Replace the Conic Plate of the AOA Sensor FIN 3FP1,

on the LH Side.

1.50

Replace the Conic Plates of the AOA Sensors FINs

3FP2 and 3FP3, on the RH Side.

3.00

Replace the AOA Protection Covers in the Flight Kit No

2 (FIN 7500NW).

0.50

Tests 0.25

Close-Up 0.50

TOTAL MANHOURS 6.25

ELAPSED TIME (HOURS) 4.25

NOTE: For detail concerning the elapsed time assumption, refer to APPENDIX 01:

Elapsed Time Assumption .

Task 345093-831-802-001: Additional Work

Get Access 0.50

On Aircraft

Modify the flat Plates position at level of the AOA

Sensors FINs 3FP2 and 3FP3, on the RH side

3.00

Tests 0.25

Close-Up 0.50

TOTAL MANHOURS 4.25

ELAPSED TIME (HOURS) 4.25

**CONF 002

Task 345093-831-801-001: Modification of the AOA sensor plates.

Get Access 0.50

On Aircraft

Replace the Conic Plate of the AOA Sensor FIN 3FP1,

on the LH Side.

1.50

Replace the Conic Plates of the AOA Sensors FINs

3FP2 and 3FP3, on the RH Side.

3.00

Replace the AOA Protection Covers in the Flight Kit No

2 (FIN 7503NW).

0.50

Tests 0.25

Close-Up 0.50

TOTAL MANHOURS 6.25

ELAPSED TIME (HOURS) 4.25

NOTE: For detail concerning the elapsed time assumption, refer to APPENDIX 01:

Elapsed Time Assumption .

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Task 345093-831-802-001: Additional Work

Get Access 0.50

On Aircraft

Modify the flat Plates position at level of the AOA

Sensors FINs 3FP2 and 3FP3, on the RH side

3.00

Tests 0.25

Close-Up 0.50

TOTAL MANHOURS 4.25

ELAPSED TIME (HOURS) 4.25

**CONF ALL

H. WEIGHT AND BALANCE

The weight and balance estimates given in this Service Bulletin are based on the

Manufacturer’s Empty Weight (MEW) and do not include operator item’s. For the definition of

(MEW) and operator’s items refer to Weight and Balance Manual (WBM) Chapter 1-00-07.

Manufacturers Empty Weight -0.549 KG (-1.2103 LB)

Effect on Balance -7.502 KGM (-54.262 LB.FT )

I. ELECTRICAL LOAD DATA

Not Changed

J. REFERENCES

**CONF 001

Aircraft Maintenance Manual (AMM) 06-20-00 06-31-53 06-41-53

12-34-24 20-21-11 20-28-00

52-30-00 52-41-00

Consumable Material List (CML)

ATA Common Support Data Dictionary (CSDD),

Chapter 2

Elec. Std. Practices Manual (ESPM) 20-51-20 20-55-00

Flight Crew Operating Manual (FCOM)

Flight Manual (FM)

Standards Manual (SM)

Structural Repair Manual (SRM) 51-24-00 51-42-00 51-43-00

Weight and Balance Manual (WBM) Chapter 1-00-07

**CONF 002

Aircraft Maintenance Manual (AMM) 06-20-00 06-31-53 06-41-53

12-34-24 20-21-11 20-28-00

52-30-00 52-41-00

Consumable Material List (CML)

ATA Common Support Data Dictionary (CSDD),

Chapter 2

Elec. Std. Practices Manual (ESPM) 20-51-20 20-55-00

DATE: Jan 30/13 SERVICE BULLETIN No.: A340-34-5093

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SERVICE BULLETIN

Flight Crew Operating Manual (FCOM)

Flight Manual (FM)

Standards Manual (SM)

Structural Repair Manual (SRM) 51-24-00 51-42-00 51-43-00

Weight and Balance Manual (WBM) Chapter 1-00-07

**CONF ALL

K. PUBLICATION AFFECTED

Aircraft Maintenance Manual (AMM) 10-11-00 12-21-11 34-11-19

Aircraft Wiring List (AWL)

Flight Crew Operating Manual (FCOM)

Flight Manual (FM)

Illustrated Parts Catalog (IPC) 25-73-04 34-11-01

Tool Equipment Manual (TEM) 10-11-00

This Service Bulletin has an operational impact. Please inform AIRBUS, at least four weeks in

advance, in case you need your operational documentation to be amended by a revision prior

to Service Bulletin embodiment. For this purpose, please request the revision by e-mail, online through the SB Reporting service or alternatively by fax to:

SEDOR4, AIRBUS

Customer Services Technical Data

Fax No.: (33) 5 61 93 28 06

E-mail: sb.reporting@airbus.com

SB Reporting service is accessible on-line through AIRBUSWorld from:

- ’My on-line services’ section, available on all AIRBUSWorld pages

- The Maintenance & Engineering Community, in:

. Modify and Upgrade page - Access SB and VSB section.

These amendments will be confirmed by the next normal revision of operational

documentation, once your Service Bulletin accomplishment report has been sent, as usual, to

our Customer Services Aircraft In-Service Data (SEDOR4).

L. INTERCHANGEABILITY/MIXABILITY

**CONF 001

DESCRIPTION OLD PART N ̊ NEW PART N ̊ INT MIXABILITY SEE

NOTES

Plate F3411060900000 F3411007920200 01 NO

Plate F3411060200000 F3411007920200 01 NO

AOA Sensor

Protection Cover

98D34203003000 98F10001000000 01 NO

Plate F3411060200000 F3411007920300 01 NO

Plate F3411060900000 F3411007920300 01 NO

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NOTE: For definitions of interchangeability codes in column INT., refer to ATA

Common Support Data Dictionary (CSDD), Chapter 2.

NOTE: Only the mixability configuration(s) and condition(s) stated in this Service

Bulletin are approved.

**CONF 002

DESCRIPTION OLD PART N ̊ NEW PART N ̊ INT MIXABILITY SEE

NOTES

Plate F3411060900000 F3411007920200 01 NO

Plate F3411060200000 F3411007920200 01 NO

AOA Sensor

Protection Cover

98D34203003000 98F10001000000 01 NO

Plate F3411060200000 F3411007920300 01 NO

Plate F3411060900000 F3411007920300 01 NO

NOTE: For definitions of interchangeability codes in column INT., refer to ATA

Common Support Data Dictionary (CSDD), Chapter 2.

NOTE: Only the mixability configuration(s) and condition(s) stated in this Service

Bulletin are approved.

**CONF ALL

M. SPARES

AOA Sensor Protection Cover 98D34203003000

Plate F3411060200000

Plate F3411060900000

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This Page Intentionally Left Blank

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SERVICE BULLETIN

2. MATERIAL INFORMATION

**CONF ALL

A. MATERIAL - PRICE AND AVAILABILITY

(1) Procurement Addresses

This Service Bulletin is the subject of an AIRBUS monitored retrofit campaign.

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:

Component COMPA01 AIRBUS Material, Logistics and Suppliers

IFD - In Flight Desk

Weg beim Jaeger 150

D-22335 HAMBOURG

GERMANY

For ordering by internet:

http://spares.airbus.com

For ordering by fax: +49 40 50 76 4012

For ordering by E-mail:

ifd.spares@airbus.com

Airbus Material, Logistics and Suppliers do not stock standard hardware as competitive

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:

Component COMPA02

Component COMPA03

B/E AEROSPACE INC

CONSUMABLES MANAGEMENT

10000 NW 15TH Terrace Miami

FL 33172

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

internet: www.beconsumables.com

or, alternatively any other source on the open

market.

(2) Price and Availability

Component COMPA01

No AIRBUS kit will be provided.

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Operator supplied AIRBUS parts required to accomplish this Service Bulletin are to be

purchased by a spares purchase order.

Operator supplied standard hardware parts required to accomplish this Service Bulletin

are to be supplied from the Operator’s stock.

Component COMPA02

No AIRBUS kit will be provided.

Operator supplied standard hardware parts required to accomplish this Service Bulletin

are to be supplied from the Operator’s stock.

Component COMPA03

No AIRBUS kit will be provided.

Operator supplied standard hardware parts required to accomplish this Service Bulletin

are to be supplied from the Operator’s stock.

B. INDUSTRY SUPPORT INFORMATION

AIRBUS will provide the AIRBUS parts (COMPA01) at no charge for orders placed before Jun

30/13.

For the accomplishment of this Service Bulletin before Jun 30/13, AIRBUS will credit the

manhours indicated in this Service Bulletin at the agreed in-house warranty labor rate for

claims received not later than 90 days after completion of the last affected aircraft of your

fleet.

For the organization of this retrofit, you are kindly requested to contact AIRBUS retrofit

management department.

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX

France

Tel : (33) 5 67 19 06 22

E-mail : monitored.retrofit@airbus.com

Fax : (33) 5 61 93 27 45

C. LIST OF COMPONENTS

No Kit

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D. LIST OF MATERIALS - OPERATOR SUPPLIED

(1) Consumable Materials

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO CML

MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant-General

Purpose Fillet

06AAB1 As required

Polysulfide Sealant-Fuel Tank Quick

Curing

06ABF1 As required

Non Aqueous Cleaner-General 08BAA9 As required

Release Agent - Liquid Wax 14DBB1 As required

(2) Components

Component COMPA01

ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE

NOTES

2 F3411007920200 1 PLATE (2) F3411060200000 01

(2) F3411060900000 01

2 F3411007920300 2 PLATE (2) F3411060200000 01

(2) F3411060900000 01

98F10001000000 3 AOAPRTCT 98D34203003000 01

NOTE: For definitions of interchangeability codes in column INT., refer to ATA

Common Support Data Dictionary (CSDD), Chapter 2.

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

Component COMPA02

ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE

NOTES

1 NAS1102-3-14 21 SCREW

3 NAS1102-3-12 2 SCREW

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.

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

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Component COMPA03

ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE

NOTES

NAS1102-3-12 2 SCREW

NAS1102-3-14 14 SCREW

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.

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

(3) Equipment

None

E. PARTS TO BE RE-IDENTIFIED BY OPERATOR

None

F. TOOLING

None

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3. ACCOMPLISHMENT INSTRUCTIONS

Task 345093-831-801-001 - Modification of the AOA sensor plates.

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

**CONF 001

Zone

121 122 160

Modified FIN

7955ME 7956ME 7957ME 7500NW

Access

Door 823

Other access Access platform

Manpower

TOTAL MANHOURS 6.25

ELAPSED TIME (HOURS) 4.25

**CONF 002

Zone

121 122 130

Modified FIN

7955ME 7956ME 7957ME 7503NW

Access

Door 821

Other access Access platform

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Manpower

TOTAL MANHOURS 6.25

ELAPSED TIME (HOURS) 4.25

**CONF ALL

A. GENERAL

**CONF 001

(1) Subtask 345093-910-001-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-20-00, Page Block 001

06-31-53, Page Block 001

Task 20-21-11-911-801

Task 20-28-00-912-802

Task 20-28-00-912-805

Consumable Material List (CML)

Elec. Std. Practices Manual (ESPM) 20-51-20

Structural Repair Manual (SRM) 51-24-00

51-42-00

51-43-00

(a) For the specification of materials (Mat. No.) given in this Service Bulletin, refer to

Consumable Materials List (CML).

(b) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001.

(c) For the identification of zones, refer to AMM 06-20-00, Page Block 001.

(d) To torque tighten the standard threaded fasteners, refer to AMM Task

20-21-11-911-801.

(e) Remove and install fasteners in accordance with SRM 51-42-00.

(f) Obtain alternative and substitute fasteners data, in accordance with SRM 51-43-00.

(g) If the length of any fastener specified in this Service Bulletin does not meet

installation standards given in SRM Chapter 51, then a fastener of the same

specification, or an approved substitute, with a length which meets the installation

standards given in SRM Chapter 51 may be used. In addition, washers may be

installed for fastener grip length in accordance with SRM Chapter 51.

(h) For the electrical bonding, refer to ESPM 20-51-20 and AMM Task

20-28-00-912-802 and/or AMM Task 20-28-00-912-805.

(i) Apply sealant in accordance with SRM 51-24-00.

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(2) Subtask 345093-839-001-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

(a) Write in the applicable aircraft records that you have done all the work given in this

Service Bulletin.

**CONF 002

(1) Subtask 345093-910-001-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-20-00, Page Block 001

06-31-53, Page Block 001

Task 20-21-11-911-801

Task 20-28-00-912-802

Task 20-28-00-912-805

Consumable Material List (CML)

Elec. Std. Practices Manual (ESPM) 20-51-20

Structural Repair Manual (SRM) 51-24-00

51-42-00

51-43-00

(a) For the specification of materials (Mat. No.) given in this Service Bulletin, refer to

Consumable Materials List (CML).

(b) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001.

(c) For the identification of zones, refer to AMM 06-20-00, Page Block 001.

(d) To torque tighten the standard threaded fasteners, refer to AMM Task

20-21-11-911-801.

(e) Remove and install fasteners in accordance with SRM 51-42-00.

(f) Obtain alternative and substitute fasteners data, in accordance with SRM 51-43-00.

(g) If the length of any fastener specified in this Service Bulletin does not meet

installation standards given in SRM Chapter 51, then a fastener of the same

specification, or an approved substitute, with a length which meets the installation

standards given in SRM Chapter 51 may be used. In addition, washers may be

installed for fastener grip length in accordance with SRM Chapter 51.

(h) For the electrical bonding, refer to ESPM 20-51-20 and AMM Task

20-28-00-912-802 and/or AMM Task 20-28-00-912-805.

(i) Apply sealant in accordance with SRM 51-24-00.

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(2) Subtask 345093-839-001-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

(a) Write in the applicable aircraft records that you have done all the work given in this

Service Bulletin.

**CONF ALL

B. PREPARATION

**CONF 001

(1) Subtask 345093-941-004-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-41-53, Page Block 001

Task 12-34-24-860-802

Task 52-30-00-010-803

52-41-00, Page Block 001

(a) Make sure that the aircraft is electrically grounded, refer to AMM Task

12-34-24-860-802.

(b) Put the access platforms in position at the Bulk cargo-compartment door 823, at

avionics compartment door 811 and at zone 121 to get access to the AOA sensor

FIN 3FP1 and at zone 122 to get access to the AOA sensors FINs 3FP2 and 3FP3.

(c) Open the Bulk cargo-compartment door 823, refer to AMM Task 52-30-00-010-803.

(d) Open the avionics compartment door 811, refer to AMM 52-41-00, Page Block 001

and AMM 06-41-53, Page Block 001.

(e) Safety precaution

1 On the panel 225VU:

a Make sure that the PROBE/WINDOW HEAT pushbutton switch is

released (the ON legend is OFF).

**CONF 002

(1) Subtask 345093-941-004-002 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

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References

Aircraft Maintenance Manual (AMM) 06-41-53, Page Block 001

Task 12-34-24-860-802

Task 52-30-00-010-801

52-41-00, Page Block 001

(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 at the FWD cargo-compartment door 821, at

avionics compartment door 811 and at zones 121 to get access to the AOA sensor

FIN 3FP1 and zone 122 to get access to the AOA sensors FINs 3FP2 and 3FP3.

(c) Open the FWD cargo-compartment door 821, refer to AMM Task

52-30-00-010-801.

(d) Open the avionics compartment door 811, refer to AMM 52-41-00, Page Block 001

and AMM 06-41-53, Page Block 001.

(e) Safety precaution

1 On the panel 225VU:

a Make sure that the PROBE/WINDOW HEAT pushbutton switch is

released (the ON legend is OFF).

**CONF ALL

C. PROCEDURE

**CONF 001

(1) Subtask 345093-831-001-001 - Replace the Conic Plate of the AOA Sensor FIN

3FP1, on the LH Side.

Work Zones and Access Panels

Zone Access/Work location

121 Access Other access Access platform

Manpower Resources

Manhours 1.50

Minimum number of person 1

Subtask elapsed time 1.50

Skills NON SPECIFIC

Material necessary to do the job

Component COMPA01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

2 F3411007920200 1 PLATE

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NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

Component COMPA02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 NAS1102-3-14 7 SCREW

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Non Aqueous CleanerGeneral08BAA9 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FBAAA

Modification of the LH side Plate

Sheet 01

Sheet 02

NOTE: The screw item (3) must not be removed to keep the AOA sensor in

position and to avoid removing it.

(a) Replace the conic plate by the flat plate of the AOA Sensor FIN 3FP1:

NOTE: Make sure that the previous plate installed on the aircraft is a conic

plate. Refer to aircraft maintenance records.

In accordance with SRM 51-42-00 and SRM 51-43-00

Refer to AMM Task 20-21-11-911-801

1 Use a non-metallic spatula to remove the sealant and clean the areas with:

Non Aqueous

Cleaner-General

08BAA9 As required

2 Remove the conic plate:

Refer to Fig. A-FBAAA Sheet 01

1 Plate F3411060200000 Item (2) Discard

or

1 Plate F3411060900000 Item (2) Discard

attached with:

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7 Screw Item (1) Discard

3 Use a non-metallic spatula to remove the sealant and clean the areas with:

Non Aqueous

Cleaner-General

08BAA9 As required

4 Install the flat plate:

CAUTION: NEW AOA FLAT PLATE SHALL NOT BE PAINTED AND

SHALL REMAIN AS DELIVERED.

NOTE: The attaching holes of the flat plates are delivered stripped

from protection at level of the surface of the bonding areas.

Refer to Fig. A-FBAAA Sheet 02

1 Plate F3411007920200 Item 2

attached with:

7 Screw NAS1102-3-14 Item 1

(2) Subtask 345093-831-002-001 - Replace the Conic Plates of the AOA Sensors FINs

3FP2 and 3FP3, on the RH Side.

Work Zones and Access Panels

Zone Access/Work location

122 Access Other access Access platform

Manpower Resources

Manhours 3.00

Minimum number of person 1

Subtask elapsed time 3.00

Skills NON SPECIFIC

Material necessary to do the job

Component COMPA01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

2 F3411007920300 2 PLATE

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

Component COMPA02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 NAS1102-3-14 14 SCREW

3 NAS1102-3-12 2 SCREW

DATE: Jan 30/13 SERVICE BULLETIN No.: A340-34-5093

REVISION No.: 01 - Jun 12/13 Page: 21

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SERVICE BULLETIN

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Non Aqueous CleanerGeneral08BAA9 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FBCAA

Modification of the RH side Plate

Sheet 01

Sheet 02

NOTE: The aim of this procedure is to keep the AOA sensors in position and to

avoid removing them.

(a) Replace the conic plates by the flat plates of the AOA Sensors FINs 3FP2 and

3FP3:

NOTE: Make sure that the previous plate installed on the aircraft is a conic

plate. Refer to aircraft maintenance records.

In accordance with SRM 51-42-00 and SRM 51-43-00

Refer to AMM Task 20-21-11-911-801

1 Use a non-metallic spatula to remove the sealant and clean the areas with:

Non Aqueous

Cleaner-General

08BAA9 As required

2 Remove the conic plates:

Refer to Fig. A-FBCAA Sheet 01

2 Plate F3411060200000 Item (2) Discard

or

2 Plate F3411060900000 Item (2) Discard

attached with:

14 Srew Item (1) Discard

3 Install the new screw item 3 in the position shown on Fig. A-FBCAA Sheet 02:

2 Screw NAS1102-3-12 Item 3

DATE: Jan 30/13 SERVICE BULLETIN No.: A340-34-5093

REVISION No.: 01 - Jun 12/13 Page: 22

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SERVICE BULLETIN

4 Remove and discard the old screw item (3) that held the AOA sensor in

position shown on Fig. A-FBCAA Sheet 02.

5 Use a non-metallic spatula to remove the sealant and clean the areas with:

Non Aqueous

Cleaner-General

08BAA9 As required

6 Install the flat plates:

CAUTION: NEW AOA FLAT PLATES SHALL NOT BE PAINTED AND

SHALL REMAIN AS DELIVERED.

NOTE: The attaching holes of the flat plates are delivered stripped

from protection at level of the surface of the bonding areas.

Refer to

2 Plate F3411007920300 Item 2

attached with:

14 Screw NAS1102-3-14 Item 1

(3) Subtask 345093-831-003-001 - Replace the AOA Protection Covers in the Flight Kit

No 2 (FIN 7500NW).

Work Zones and Access Panels

Zone Access/Work location

160 Access Door 823

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills NON SPECIFIC

Material necessary to do the job

Component COMPA01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

98F10001000000 3 AOAPRTCT

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

References

Fig. A-FBBAA

Modification of AOA Protection Covers in

the Flight Kit No 2

Sheet 01

DATE: Jan 30/13 SERVICE BULLETIN No.: A340-34-5093

REVISION No.: 01 - Jun 12/13 Page: 23

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NOTE: Depending on airline internal policy the Flight Kit No 2 may not be

located in the place defined by Fig. A-FBBAA Sheet 01. Refer to airline

internal policy for exact location for Flight Kit No 2 and/or its contents.

(a) Remove in the Flight Kit No 2 (FIN 7500NW):

Refer to Fig. A-FBBAA Sheet 01:

FIN 7955ME

1 AOA Sensor Protection

Cover

98D34203003000 Discard

FIN 7956ME

1 AOA Sensor Protection

Cover

98D34203003000 Discard

FIN 7957ME

1 AOA Sensor Protection

Cover

98D34203003000 Discard

(b) Install in the Flight Kit No 2 (FIN 7500NW):

Fig. A-FBBAA Sheet 01:

FIN 7955ME

1 AOA Sensor Protection

Cover

98F10001000000

FIN 7956ME

1 AOA Sensor Protection

Cover

98F10001000000

FIN 7957ME

1 AOA Sensor Protection

Cover

98F10001000000

**CONF 002

(1) Subtask 345093-831-001-001 - Replace the Conic Plate of the AOA Sensor FIN

3FP1, on the LH Side.

Work Zones and Access Panels

Zone Access/Work location

121 Access Other access Access platform

Manpower Resources

Manhours 1.50

Minimum number of person 1

Subtask elapsed time 1.50

Skills NON SPECIFIC

DATE: Jan 30/13 SERVICE BULLETIN No.: A340-34-5093

REVISION No.: 01 - Jun 12/13 Page: 24

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SERVICE BULLETIN

Material necessary to do the job

Component COMPA01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

2 F3411007920200 1 PLATE

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

Component COMPA02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 NAS1102-3-14 7 SCREW

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Non Aqueous CleanerGeneral08BAA9 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FBAAA

Modification of the LH side Plate

Sheet 01

Sheet 02

NOTE: The screw item (3) must not be removed to keep the AOA sensor in

position and to avoid removing it.

(a) Replace the conic plate by the flat plate of the AOA Sensor FIN 3FP1:

NOTE: Make sure that the previous plate installed on the aircraft is a conic

plate. Refer to aircraft maintenance records.

In accordance with SRM 51-42-00 and SRM 51-43-00

Refer to AMM Task 20-21-11-911-801

1 Use a non-metallic spatula to remove the sealant and clean the areas with:

Non Aqueous

Cleaner-General

08BAA9 As required

2 Remove the conic plate:

Refer to Fig. A-FBAAA Sheet 01

DATE: Jan 30/13 SERVICE BULLETIN No.: A340-34-5093

REVISION No.: 01 - Jun 12/13 Page: 25

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1 Plate F3411060200000 Item (2) Discard

or

1 Plate F3411060900000 Item (2) Discard

attached with:

7 Screw Item (1) Discard

3 Use a non-metallic spatula to remove the sealant and clean the areas with:

Non Aqueous

Cleaner-General

08BAA9 As required

4 Install the flat plate:

CAUTION: NEW AOA FLAT PLATE SHALL NOT BE PAINTED AND

SHALL REMAIN AS DELIVERED.

NOTE: The attaching holes of the flat plates are delivered stripped

from protection at level of the surface of the bonding areas.

Refer to Fig. A-FBAAA Sheet 02

1 Plate F3411007920200 Item 2

attached with:

7 Screw NAS1102-3-14 Item 1

(2) Subtask 345093-831-002-001 - Replace the Conic Plates of the AOA Sensors FINs

3FP2 and 3FP3, on the RH Side.

Work Zones and Access Panels

Zone Access/Work location

122 Access Other access Access platform

Manpower Resources

Manhours 3.00

Minimum number of person 1

Subtask elapsed time 3.00

Skills NON SPECIFIC

Material necessary to do the job

Component COMPA01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

2 F3411007920300 2 PLATE

DATE: Jan 30/13 SERVICE BULLETIN No.: A340-34-5093

REVISION No.: 01 - Jun 12/13 Page: 26

5

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@A340-500/600

SERVICE BULLETIN

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

Component COMPA02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 NAS1102-3-14 14 SCREW

3 NAS1102-3-12 2 SCREW

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Non Aqueous CleanerGeneral08BAA9 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FBCAA

Modification of the RH side Plate

Sheet 01

Sheet 02

NOTE: The aim of this procedure is to keep the AOA sensors in position and to

avoid removing them.

(a) Replace the conic plates by the flat plates of the AOA Sensors FINs 3FP2 and

3FP3:

NOTE: Make sure that the previous plate installed on the aircraft is a conic

plate. Refer to aircraft maintenance records.

In accordance with SRM 51-42-00 and SRM 51-43-00

Refer to AMM Task 20-21-11-911-801

1 Use a non-metallic spatula to remove the sealant and clean the areas with:

Non Aqueous

Cleaner-General

08BAA9 As required

2 Remove the conic plates:

Refer to Fig. A-FBCAA Sheet 01

2 Plate F3411060200000 Item (2) Discard

or

2 Plate F3411060900000 Item (2) Discard

DATE: Jan 30/13 SERVICE BULLETIN No.: A340-34-5093

REVISION No.: 01 - Jun 12/13 Page: 27

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@A340-500/600

SERVICE BULLETIN

attached with:

14 Srew Item (1) Discard

3 Install the new screw item 3 in the position shown on Fig. A-FBCAA Sheet 02:

2 Screw NAS1102-3-12 Item 3

4 Remove and discard the old screw item (3) that held the AOA sensor in

position shown on Fig. A-FBCAA Sheet 02.

5 Use a non-metallic spatula to remove the sealant and clean the areas with:

Non Aqueous

Cleaner-General

08BAA9 As required

6 Install the flat plates:

CAUTION: NEW AOA FLAT PLATES SHALL NOT BE PAINTED AND

SHALL REMAIN AS DELIVERED.

NOTE: The attaching holes of the flat plates are delivered stripped

from protection at level of the surface of the bonding areas.

Refer to

2 Plate F3411007920300 Item 2

attached with:

14 Screw NAS1102-3-14 Item 1

(3) Subtask 345093-831-003-002 - Replace the AOA Protection Covers in the Flight Kit

No 2 (FIN 7503NW).

Work Zones and Access Panels

Zone Access/Work location

130 Access Door 821

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills NON SPECIFIC

Material necessary to do the job

Component COMPA01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

98F10001000000 3 AOAPRTCT

DATE: Jan 30/13 SERVICE BULLETIN No.: A340-34-5093

REVISION No.: 01 - Jun 12/13 Page: 28

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@A340-500/600

SERVICE BULLETIN

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

References

Fig. A-FBBAB

Modification of AOA Protection Covers in

the Flight Kit No 2

Sheet 01

NOTE: Depending on airline internal policy the Flight Kit No 2 may not be

located in the place defined by Fig. A-FBBAB Sheet 01. Refer to airline

internal policy for exact location for Flight Kit No 2 and/or its contents.

(a) Remove in the Flight Kit No 2 (FIN 7503NW):

Refer to Fig. A-FBBAB Sheet 01:

FIN 7955ME

1 AOA Sensor Protection

Cover

98D34203003000 Discard

FIN 7956ME

1 AOA Sensor Protection

Cover

98D34203003000 Discard

FIN 7957ME

1 AOA Sensor Protection

Cover

98D34203003000 Discard

(b) Install in the Flight Kit No 2 (FIN 7503NW):

Refer to Fig. A-FBBAB Sheet 01

FIN 7955ME

1 AOA Sensor Protection

Cover

98F10001000000

FIN 7956ME

1 AOA Sensor Protection

Cover

98F10001000000

FIN 7957ME

1 AOA Sensor Protection

Cover

98F10001000000

DATE: Jan 30/13 SERVICE BULLETIN No.: A340-34-5093

REVISION No.: 01 - Jun 12/13 Page: 29

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SERVICE BULLETIN

**CONF ALL

D. TEST

**CONF 001

(1) Subtask 345093-700-001-001 - Testing

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 20-28-00-720-805

Task 20-28-00-869-801

(a) Test of electrical bonding at level of the screw item 3:

1 Make sure that the bonding contact resistance between the sensor (via screw

item 3) and the fuselage structure is not higher than 5 milliohms, refer to AMM

Task 20-28-00-720-805.

**CONF 002

(1) Subtask 345093-700-001-001 - Testing

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 20-28-00-720-805

Task 20-28-00-869-801

(a) Test of electrical bonding at level of the screw item 3:

1 Make sure that the bonding contact resistance between the sensor (via screw

item 3) and the fuselage structure is not higher than 5 milliohms, refer to AMM

Task 20-28-00-720-805.

**CONF ALL

E. CLOSE-UP

**CONF 001

(1) Subtask 345093-942-001-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

DATE: Jan 30/13 SERVICE BULLETIN No.: A340-34-5093

REVISION No.: 01 - Jun 12/13 Page: 30

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Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant-General

Purpose Fillet

06AAB1 As required

Polysulfide Sealant-Fuel

Tank Quick Curing

06ABF1 As required

Release Agent - Liquid Wax 14DBB1 As required

References

Aircraft Maintenance Manual (AMM) 06-41-53, Page Block 001

Task 20-28-00-912-802

Task 20-28-00-912-804

Task 52-30-00-410-803

52-41-00, Page Block 001

Elec. Std. Practices Manual (ESPM) 20-51-20

Structural Repair Manual (SRM) 51-24-00

Fig. A-FBAAA

Modification of the LH side Plate

Sheet 01

Sheet 02

Fig. A-FBCAA

Modification of the RH side Plate

Sheet 01

Sheet 02

(a) Protect the screws item 1 and item 3 in accordance with ESPM 20-51-20 and AMM

Task 20-28-00-912-802 and/or AMM Task 20-28-00-912-804.

(b) Blank off the hole located in front of the screw item (3) in accordance with SRM

51-24-00 and as shown on Fig. A-FBAAA Sheet 02 and on Fig. A-FBCAA Sheet 02

with:

Release Agent -

Liquid Wax

14DBB1 As required

and

Polysulfide SealantGeneral Purpose

Fillet

06AAB1 As required

or

Polysulfide SealantFuel Tank Quick

Curing

06ABF1 As required

(c) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(d) Close the Bulk cargo-compartment door 823, refer to AMM Task 52-30-00-410-803.

DATE: Jan 30/13 SERVICE BULLETIN No.: A340-34-5093

REVISION No.: 01 - Jun 12/13 Page: 31

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(e) Close the avionics compartment door 811, refer to AMM 06-41-53, Page Block 001

and AMM 52-41-00, Page Block 001.

(f) Remove the access platform(s).

(g) Restore the systems and the aircraft to normal operating condition.

**CONF 002

(1) Subtask 345093-942-001-002 - Close-up

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

Polysulfide Sealant-General

Purpose Fillet

06AAB1 As required

Polysulfide Sealant-Fuel

Tank Quick Curing

06ABF1 As required

Release Agent - Liquid Wax 14DBB1 As required

References

Aircraft Maintenance Manual (AMM) 06-41-53, Page Block 001

Task 20-28-00-912-802

Task 20-28-00-912-804

Task 52-30-00-410-801

52-41-00, Page Block 001

Elec. Std. Practices Manual (ESPM) 20-51-20

Structural Repair Manual (SRM) 51-24-00

Fig. A-FBAAA

Modification of the LH side Plate

Sheet 01

Sheet 02

Fig. A-FBCAA

Modification of the RH side Plate

Sheet 01

Sheet 02

(a) Protect the screws item 1 and item 3 in accordance with ESPM 20-51-20 and AMM

Task 20-28-00-912-802 and/or AMM Task 20-28-00-912-804.

(b) Blank off the hole located in front of the screw item (3) in accordance with SRM

51-24-00 and as shown on Fig. A-FBAAA Sheet 02 and on Fig. A-FBCAA Sheet 02

with:

Release Agent -

Liquid Wax

14DBB1 As required

and

DATE: Jan 30/13 SERVICE BULLETIN No.: A340-34-5093

REVISION No.: 01 - Jun 12/13 Page: 32

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SERVICE BULLETIN

Polysulfide SealantGeneral Purpose

Fillet

06AAB1 As required

or

Polysulfide SealantFuel Tank Quick

Curing

06ABF1 As required

(c) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(d) Close the FWD cargo-compartment door 821, refer to AMM Task

52-30-00-410-801.

(e) Close the avionics compartment door 811, refer to AMM 06-41-53, Page Block 001

and AMM 52-41-00, Page Block 001.

(f) Remove the access platform(s).

(g) Restore the systems and the aircraft to normal operating condition.

DATE: Jan 30/13 SERVICE BULLETIN No.: A340-34-5093

REVISION No.: 01 - Jun 12/13 Page: 33

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This Page Intentionally Left Blank

DATE: Jan 30/13 SERVICE BULLETIN No.: A340-34-5093

REVISION No.: 01 - Jun 12/13 Page: 34

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SERVICE BULLETIN

Task 345093-831-802-001 - Additional Work

**CONF ALL

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

**CONF 001

Zone

120

Access

Other access Access Platform

Manpower

TOTAL MANHOURS 4.25

ELAPSED TIME (HOURS) 4.25

**CONF 002

Zone

120

Access

Other access Access Platform

Manpower

TOTAL MANHOURS 4.25

ELAPSED TIME (HOURS) 4.25

DATE: Jan 30/13 SERVICE BULLETIN No.: A340-34-5093

REVISION No.: 01 - Jun 12/13 Page: 35

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SERVICE BULLETIN

**CONF ALL

A. GENERAL

**CONF 001

(1) Subtask 345093-910-002-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-20-00, Page Block 001

06-31-53, Page Block 001

Task 20-21-11-911-801

Task 20-28-00-912-804

Task 20-28-00-912-805

Consumable Material List (CML)

Elec. Std. Practices Manual (ESPM) 20-51-20

Structural Repair Manual (SRM) 51-24-00

51-42-00

51-43-00

(a) For the specification of the materials (Mat. No.) given in this Service Bulletin, refer

to Consumable Material List (CML).

(b) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001.

(c) For the identification of zones, refer to AMM 06-20-00, Page Block 001.

(d) To torque tighten the standard threaded fasteners, refer to AMM Task

20-21-11-911-801.

(e) Remove and install of fasteners in accordance with SRM 51-42-00.

(f) Obtain alternative and substitute fastener data in accordance with SRM 51-43-00.

(g) If the length of any fastener specified in this Service Bulletin does not meet

installation standards given in SRM Chapter 51, then a fastener of the same

specification, or an approved substitute, with a length which meets the installation

standards given in SRM Chapter 51 may be used. In addition, washers may be

installed for fastener grip length in accordance with SRM Chapter 51.

(h) Do the electrical bonding, refer to ESPM 20-51-20 and AMM Task

20-28-00-912-804 or AMM Task 20-28-00-912-805.

(i) Apply sealant in accordance with SRM 51-24-00.

(2) Subtask 345093-839-002-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

DATE: Jan 30/13 SERVICE BULLETIN No.: A340-34-5093

REVISION No.: 01 - Jun 12/13 Page: 36

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SERVICE BULLETIN

Write in the applicable aircraft records that you have done all the work given in this

Service Bulletin.

**CONF 002

(1) Subtask 345093-910-002-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-20-00, Page Block 001

06-31-53, Page Block 001

Task 20-21-11-911-801

Task 20-28-00-912-804

Task 20-28-00-912-805

Consumable Material List (CML)

Elec. Std. Practices Manual (ESPM) 20-51-20

Structural Repair Manual (SRM) 51-24-00

51-42-00

51-43-00

(a) For the specification of the materials (Mat. No.) given in this Service Bulletin, refer

to Consumable Material List (CML).

(b) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001.

(c) For the identification of zones, refer to AMM 06-20-00, Page Block 001.

(d) To torque tighten the standard threaded fasteners, refer to AMM Task

20-21-11-911-801.

(e) Remove and install of fasteners in accordance with SRM 51-42-00.

(f) Obtain alternative and substitute fastener data in accordance with SRM 51-43-00.

(g) If the length of any fastener specified in this Service Bulletin does not meet

installation standards given in SRM Chapter 51, then a fastener of the same

specification, or an approved substitute, with a length which meets the installation

standards given in SRM Chapter 51 may be used. In addition, washers may be

installed for fastener grip length in accordance with SRM Chapter 51.

(h) Do the electrical bonding, refer to ESPM 20-51-20 and AMM Task

20-28-00-912-804 or AMM Task 20-28-00-912-805.

(i) Apply sealant in accordance with SRM 51-24-00.

(2) Subtask 345093-839-002-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

DATE: Jan 30/13 SERVICE BULLETIN No.: A340-34-5093

REVISION No.: 01 - Jun 12/13 Page: 37

5

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@A340-500/600

SERVICE BULLETIN

Write in the applicable aircraft records that you have done all the work given in this

Service Bulletin.

**CONF ALL

B. PREPARATION

**CONF 001

(1) Subtask 345093-941-002-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-41-53, Page Block 001

Task 12-34-24-860-802

52-41-00, Page Block 001

(a) Make sure that the aircraft is electrically grounded, refer to AMM Task

12-34-24-860-802.

(b) Put the access platforms in position at the avionics compartment door 811 and at

zone 122 to get access to the AOA sensors (FINs 3FP2 and 3FP3).

(c) Open the avionics compartment door 811, refer to AMM 06-41-53, Page Block 001

and AMM 52-41-00, Page Block 001.

(d) Safety precaution

1 On the panel 225VU:

a Make sure that the PROBE/WINDOW HEAT pushbutton switch is

released (the ON legend is OFF).

**CONF 002

(1) Subtask 345093-941-002-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-41-53, Page Block 001

Task 12-34-24-860-802

52-41-00, Page Block 001

(a) Make sure that the aircraft is electrically grounded, refer to AMM Task

12-34-24-860-802.

(b) Put the access platforms in position at the avionics compartment door 811 and at

zone 122 to get access to the AOA sensors (FINs 3FP2 and 3FP3).

DATE: Jan 30/13 SERVICE BULLETIN No.: A340-34-5093

REVISION No.: 01 - Jun 12/13 Page: 38

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(c) Open the avionics compartment door 811, refer to AMM 06-41-53, Page Block 001

and AMM 52-41-00, Page Block 001.

(d) Safety precaution

1 On the panel 225VU:

a Make sure that the PROBE/WINDOW HEAT pushbutton switch is

released (the ON legend is OFF).

**CONF ALL

C. PROCEDURE

**CONF 001

(1) Subtask 345093-831-004-001 - Modify the flat Plates position at level of the AOA

Sensors FINs 3FP2 and 3FP3, on the RH side

Work Zones and Access Panels

Zone Access/Work location

120 Access Other access Access Platform

Manpower Resources

Manhours 3.00

Minimum number of person 1

Subtask elapsed time 3.00

Skills NON SPECIFIC

Material necessary to do the job

Component COMPA03

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

NAS1102-3-12 2 SCREW

NAS1102-3-14 14 SCREW

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Non Aqueous CleanerGeneral08BAA9 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

DATE: Jan 30/13 SERVICE BULLETIN No.: A340-34-5093

REVISION No.: 01 - Jun 12/13 Page: 39

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References

Fig. A-FBDAA

Modification of the RH side Plate

(Additional Work)

Sheet 01

Sheet 02

(a) If screw item (3) is located as shown on Fig. A-FBDAA Sheet 02:

1 No further action is required.

(b) If screw item (3) is NOT located as shown on Fig. A-FBDAA Sheet 02:

NOTE: The aim of this procedure is to change the position of the screw

item 3 keeping AOA sensor in the same position.

In accordance with SRM 51-42-00 and SRM 51-43-00

Refer to AMM Task 20-21-11-911-801

1 Use a non-metallic spatula to remove the sealant and clean the areas with:

Non Aqueous

Cleaner-General

08BAA9 As required

2 Remove the flat plates:

2 Plate F3411007920300 Item (2) Retain

attached with:

14 Screw Item (1) Discard

3 Install the new screw item 3 in the position shown on Fig. A-FBDAA Sheet 02:

2 Screw NAS1102-3-12

4 Remove and discard the old screw item (3) that held the AOA sensor in

position shown on Fig. A-FBDAA Sheet 01.

5 Re-install the flat plates item (2) retained at removal:

CAUTION: NEW AOA FLAT PLATES SHALL NOT BE PAINTED AND

SHALL REMAIN AS DELIVERED

Refer to Fig. A-FBDAA Sheet 02:

2 Plate F3411007920300 Item (2) Retained at

removal

attached with:

14 Screw NAS1102-3-14

DATE: Jan 30/13 SERVICE BULLETIN No.: A340-34-5093

REVISION No.: 01 - Jun 12/13 Page: 40

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**CONF 002

(1) Subtask 345093-831-004-001 - Modify the flat Plates position at level of the AOA

Sensors FINs 3FP2 and 3FP3, on the RH side

Work Zones and Access Panels

Zone Access/Work location

120 Access Other access Access Platform

Manpower Resources

Manhours 3.00

Minimum number of person 1

Subtask elapsed time 3.00

Skills NON SPECIFIC

Material necessary to do the job

Component COMPA03

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

NAS1102-3-12 2 SCREW

NAS1102-3-14 14 SCREW

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Non Aqueous CleanerGeneral08BAA9 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FBDAA

Modification of the RH side Plate

(Additional Work)

Sheet 01

Sheet 02

(a) If screw item (3) is located as shown on Fig. A-FBDAA Sheet 02:

1 No further action is required.

(b) If screw item (3) is NOT located as shown on Fig. A-FBDAA Sheet 02:

NOTE: The aim of this procedure is to change the position of the screw

item 3 keeping AOA sensor in the same position.

In accordance with SRM 51-42-00 and SRM 51-43-00

DATE: Jan 30/13 SERVICE BULLETIN No.: A340-34-5093

REVISION No.: 01 - Jun 12/13 Page: 41

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Refer to AMM Task 20-21-11-911-801

1 Use a non-metallic spatula to remove the sealant and clean the areas with:

Non Aqueous

Cleaner-General

08BAA9 As required

2 Remove the flat plates:

2 Plate F3411007920300 Item (2) Retain

attached with:

14 Screw Item (1) Discard

3 Install the new screw item 3 in the position shown on Fig. A-FBDAA Sheet 02:

2 Screw NAS1102-3-12

4 Remove and discard the old screw item (3) that held the AOA sensor in

position shown on Fig. A-FBDAA Sheet 01.

5 Re-install the flat plates item (2) retained at removal:

CAUTION: NEW AOA FLAT PLATES SHALL NOT BE PAINTED AND

SHALL REMAIN AS DELIVERED

Refer to Fig. A-FBDAA Sheet 02:

2 Plate F3411007920300 Item (2) Retained at

removal

attached with:

14 Screw NAS1102-3-14

**CONF ALL

D. TEST

**CONF 001

(1) Subtask 345093-700-002-001 - Testing

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 20-28-00-720-805

Task 20-28-00-869-801

DATE: Jan 30/13 SERVICE BULLETIN No.: A340-34-5093

REVISION No.: 01 - Jun 12/13 Page: 42

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(a) Test of electrical bonding at level of the screw item 3:

1 Make sure that the bonding contact resistance between the sensor (via screw

item 3) and the fuselage structure is not higher than 5 milliohms, refer to AMM

Task 20-28-00-720-805.

**CONF 002

(1) Subtask 345093-700-002-001 - Testing

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 20-28-00-720-805

Task 20-28-00-869-801

(a) Test of electrical bonding at level of the screw item 3:

1 Make sure that the bonding contact resistance between the sensor (via screw

item 3) and the fuselage structure is not higher than 5 milliohms, refer to AMM

Task 20-28-00-720-805.

**CONF ALL

E. CLOSE-UP

**CONF 001

(1) Subtask 345093-942-002-001 - Close-up

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

Polysulfide Sealant-General

Purpose Fillet

06AAB1 As required

Polysulfide Sealant-Fuel

Tank Quick Curing

06ABF1 As required

Release Agent - Liquid Wax 14DBB1 As required

References

Aircraft Maintenance Manual (AMM) 06-41-53, Page Block 001

Task 20-28-00-912-802

Task 20-28-00-912-804

52-41-00, Page Block 001

Elec. Std. Practices Manual (ESPM) 20-51-20

DATE: Jan 30/13 SERVICE BULLETIN No.: A340-34-5093

REVISION No.: 01 - Jun 12/13 Page: 43

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References

Structural Repair Manual (SRM) 51-24-00

Fig. A-FBDAA

Modification of the RH side Plate

(Additional Work)

Sheet 01

Sheet 02

(a) Protect the screws item 1 and item 3 in accordance with ESPM 20-51-20 and AMM

Task 20-28-00-912-802 and/or AMM Task 20-28-00-912-804.

(b) Blank off the hole located in front of the screw item (3) in accordance with SRM

51-24-00 as shown on Fig. A-FBDAA Sheet 02 with:

Release Agent -

Liquid Wax

14DBB1 As required

and

Polysulfide SealantGeneral Purpose

Fillet

06AAB1 As required

or

Polysulfide SealantFuel Tank Quick

Curing

06ABF1 As required

(c) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(d) Close the avionics compartment door 811, refer to AMM 06-41-53, Page Block 001

and AMM 52-41-00, Page Block 001.

(e) Remove the access platform(s).

(f) Restore the systems and the aircraft to normal operating condition.

**CONF 002

(1) Subtask 345093-942-002-001 - Close-up

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

Polysulfide Sealant-General

Purpose Fillet

06AAB1 As required

DATE: Jan 30/13 SERVICE BULLETIN No.: A340-34-5093

REVISION No.: 01 - Jun 12/13 Page: 44

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ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant-Fuel

Tank Quick Curing

06ABF1 As required

Release Agent - Liquid Wax 14DBB1 As required

References

Aircraft Maintenance Manual (AMM) 06-41-53, Page Block 001

Task 20-28-00-912-802

Task 20-28-00-912-804

52-41-00, Page Block 001

Elec. Std. Practices Manual (ESPM) 20-51-20

Structural Repair Manual (SRM) 51-24-00

Fig. A-FBDAA

Modification of the RH side Plate

(Additional Work)

Sheet 01

Sheet 02

(a) Protect the screws item 1 and item 3 in accordance with ESPM 20-51-20 and AMM

Task 20-28-00-912-802 and/or AMM Task 20-28-00-912-804.

(b) Blank off the hole located in front of the screw item (3) in accordance with SRM

51-24-00 as shown on Fig. A-FBDAA Sheet 02 with:

Release Agent -

Liquid Wax

14DBB1 As required

and

Polysulfide SealantGeneral Purpose

Fillet

06AAB1 As required

or

Polysulfide SealantFuel Tank Quick

Curing

06ABF1 As required

(c) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(d) Close the avionics compartment door 811, refer to AMM 06-41-53, Page Block 001

and AMM 52-41-00, Page Block 001.

(e) Remove the access platform(s).

(f) Restore the systems and the aircraft to normal operating condition.

DATE: Jan 30/13 SERVICE BULLETIN No.: A340-34-5093

REVISION No.: 01 - Jun 12/13 Page: 45

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**CONF ALL

BEFORE

FR19

FR18

3FP1

A

(7 POS) (1) (7 POS) (1)

OR

(2) (2)

(3) (3)

NOTE:

TYPICAL ILLUSTRATION ASSOCIATED WITH THALES OR GOODRICH AOA SENSORS.

THALES GOODRICH

A B

F_SB_345093_5_BAAA_01_02

Figure A-FBAAA - Sheet 01

Modification of the LH side Plate

DATE: Jan 30/13 SERVICE BULLETIN No.: A340-34-5093

REVISION No.: 01 - Jun 12/13 Page: 46

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SERVICE BULLETIN

**CONF ALL

AFTER

1

2

(7 POS)

(3)

NOTE:

ONLY ONE CONFIGURATION SHOWN, AOA SENSOR

01 BLANK OFF THE HOLE LOCATED IN FRONT OF THE SCREW ITEM WITH:

MAT. No 14DBB1 AND MAT. No 06ABF1 OR 06AAB1.

(3)

DEPENDS ON AIRCRAFT CONFIGURATION.

01

B

ELECTRICAL BONDING

F_SB_345093_5_BAAA_02_04

Figure A-FBAAA - Sheet 02

Modification of the LH side Plate

DATE: Jan 30/13 SERVICE BULLETIN No.: A340-34-5093

REVISION No.: 01 - Jun 12/13 Page: 47

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**CONF ALL

BEFORE

FR19

FR18

3FP2

3FP3

A B

A B

A

OR

NOTE:

TYPICAL ILLUSTRATION ASSOCIATED WITH THALES OR GOODRICH AOA SENSORS.

THALES GOODRICH

(1)(7 POS)

(2)

(3)

(1)(7 POS)

(2)

(3)

F_SB_345093_5_BCAA_01_00

Figure A-FBCAA - Sheet 01

Modification of the RH side Plate

DATE: Jan 30/13 SERVICE BULLETIN No.: A340-34-5093

REVISION No.: 01 - Jun 12/13 Page: 48

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**CONF ALL

AFTER

NOTE:

ONLY ONE CONFIGURATION SHOWN, AOA SENSOR

01 BLANK OFF THE HOLE LOCATED IN FRONT OF THE SCREW ITEM WITH:

MAT. No 14DBB1 AND MAT. No 06ABF1 OR 06AAB1.

3

DEPENDS ON AIRCRAFT CONFIGURATION.

B

ELECTRICAL BONDING

1

2

(7 POS)

3 01

F_SB_345093_5_BCAA_02_00

Figure A-FBCAA - Sheet 02

Modification of the RH side Plate

DATE: Jan 30/13 SERVICE BULLETIN No.: A340-34-5093

REVISION No.: 01 - Jun 12/13 Page: 49

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**CONF 001

B

FR69

FR73

A

A

Z160

B

7500NW

FLIGHT KIT No 2

NOTE:

ARE STORED IN FLIGHT KIT No 2 FIN (7500NW)

AOA PROTECTION COVERS FINs (7955ME, 7956ME AND 7957ME)

F_SB_345093_5_BBAA_01_02

Figure A-FBBAA - Sheet 01

Modification of AOA Protection Covers in the Flight Kit No 2

DATE: Jan 30/13 SERVICE BULLETIN No.: A340-34-5093

REVISION No.: 01 - Jun 12/13 Page: 50

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**CONF 002

A

A

Z130

FR20

FR25

FR26

B

FLIGHT KIT No 2

NOTE:

ARE STORED IN FLIGHT KIT No 2 FIN (7503NW)

AOA PROTECTION COVERS FINs (7955ME, 7956ME AND 7957ME)

B

7503NW

F_SB_345093_5_BBAB_01_02

Figure A-FBBAB - Sheet 01

Modification of AOA Protection Covers in the Flight Kit No 2

DATE: Jan 30/13 SERVICE BULLETIN No.: A340-34-5093

REVISION No.: 01 - Jun 12/13 Page: 51

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**CONF ALL

BEFORE

FR19

FR18

3FP2

3FP3

A B

A B

A

(1)

(2)

(7 POS)

(3) 01

NOTE:

TYPICAL ILLUSTRATION ASSOCIATED WITH THALES OR GOODRICH AOA SENSORS.

F_SB_345093_5_BDAA_01_00

Figure A-FBDAA - Sheet 01

Modification of the RH side Plate (Additional Work)

DATE: Jan 30/13 SERVICE BULLETIN No.: A340-34-5093

REVISION No.: 01 - Jun 12/13 Page: 52

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**CONF ALL

AFTER

NOTE:

ONLY ONE CONFIGURATION SHOWN, AOA SENSOR

01 BLANK OFF THE HOLE LOCATED IN FRONT OF THE SCREW ITEM WITH:

MAT. No 14DBB1 AND MAT. No 06ABF1 OR 06AAB1.

3

DEPENDS ON AIRCRAFT CONFIGURATION.

B

ELECTRICAL BONDING

1

2

(7 POS)

3 01

F_SB_345093_5_BDAA_02_00

Figure A-FBDAA - Sheet 02

Modification of the RH side Plate (Additional Work)

DATE: Jan 30/13 SERVICE BULLETIN No.: A340-34-5093

REVISION No.: 01 - Jun 12/13 Page: 53

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This Page Intentionally Left Blank

DATE: Jan 30/13 SERVICE BULLETIN No.: A340-34-5093

REVISION No.: 01 - Jun 12/13 Page: 54

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SERVICE BULLETIN

APPENDIX 01: Elapsed Time Assumption

**CONF ALL

(1) The following Gantt chart is only a proposal operators may determine that another way to do the

work is more suitable for them.

DATE: Jan 30/13 SERVICE BULLETIN No.: A340-34-5093

REVISION No.: 01 - Jun 12/13 Page: 1

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APPENDIX 01: Elapsed Time Assumption

**CONF ALL

ELAPSED TIME ASSUMPTION SERVICE BULLETIN No A340−34−5093

GET ACCESS

MH ET/S

TOTAL MANHOURS

SB ELAPSED TIME

6.25

4.25

STEPS

0.50 0.50

0 5

1.50 1.50

3.00 3.00

TEST 0.25 0.25

CLOSE−UP 0.50 0.50

MH

ET/S:

PER

MANHOURS

ELAPSED TIME PER STEP

NUMBER OF PERSONS

01

02

THIS CHART IS ONLY A PROPOSAL.

OPERATORS MAY DETERMINE THAT ANOTHER WAY

TO DO THE WORK IS MORE SUITABLE FOR THEM.

01

02

NOTE:

PER

1

1

1

1

1

REPLACEMENT OF AOA PROTECTION 0.50 0.50 1

:

:

SB ELAPSED TIME

(HOURS)

1 2 3 4

IF A VSB IS INVOLVED, THE ASSOCIATED MANHOURS

ARE NOT REFLECTED IN THIS GANTT CHART.

COVERS IN THE FLIGHT KIT No 2

REPLACEMENT OF THE PLATE OF

THE AOA SENSOR FIN 3FP1, RH SIDE

REPLACEMENT OF THE PLATE OF

THE AOA SENSOR FINs 3FP2 AND

3FP3, LH SIDE

F_SB_345093_5_AAAA_01_01

Figure A-FAAAA - Sheet 01

Gantt Chart

DATE: Jan 30/13 SERVICE BULLETIN No.: A340-34-5093

REVISION No.: 01 - Jun 12/13 Page: 2

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REPORTING SHEET

TITLE: NAVIGATION - GENERAL - REPLACE AOA PROBE CONIC PLATE BY

AOA PROBE FLAT PLATE

MODIFICATION No.: 203295S32646

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: Jan 30/13 SERVICE BULLETIN No.: A340-34-5093

REVISION No.: 01 - Jun 12/13 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 4321

- Quality rating of the Accomplishment Instructions 4321

- Quality rating of the Illustrations 4321

- Is this SB easy to understand ? Y/N

If you have had difficulties in the accomplishment of this SB please quote below the area(s) and give a

short description of the issue.

Planning Material Instructions

X Effectivity X Kit content X Preparation

X Reason X List of Materials Operator Supplied X Mod/Inspection

X Manpower X Industry support X Test

X References X Re-identification X Close-Up

X Publication X Tooling X Illustrations

Comments:

Operator: Date:

Name/Title:

Please return this form to:

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX FRANCE

Attn : SEM4 Service Bulletins Management

FAX : (33) 5 61 93 42 51

Or via your Resident Customer Support Office.

DATE: Jan 30/13 SERVICE BULLETIN No.: A340-34-5093

REVISION No.: 01 - Jun 12/13 Page: 1

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