@A340

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

ATA SYSTEM: 36

TITLE: PNEUMATIC - LEAK DETECTION - INTRODUCE ADAPTED DUAL LOOP

OVERHEAT LEAK DETECTION APU BLEED AIR DUCT

MODIFICATION No.: 55198D46290 55198D46286 55961D46493 55962D46494 58529D46961

58530D46962

This page transmits Revision No.01 of Service Bulletin No.A340-36-4033

ADDITIONAL WORK

**CONF ALL

No additional work is required by this revision for aircraft modified by any previous issue.

REASON

Revision No. 01 issued to:

- integrate the results of the validation of the equivalent of this Service Bulletin, accomplished on

A330 aircraft MSN 0389,

- introduce minor changes.

CHANGES

SUMMARY

MATERIAL PRICE INFORMATION MATERIAL PRICE INFORMATION TABLE

UPDATED

R

MATERIAL PRICE INFORMATION TABLE

UPDATED

R

MATERIAL PRICE INFORMATION TABLE

UPDATED

R

MATERIAL PRICE INFORMATION TABLE

UPDATED

R

MATERIAL PRICE INFORMATION TABLE

UPDATED

R

EFFECTIVITY OPERATOR LIST UPDATED R

PLANNING INFORMATION

EFFECTIVITY EFFECTIVITY RELATED INFORMATION

UPDATED

R

Configuration definition

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 1

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

CONF 001 CONFIGURATION DEFINITION UPDATED R

Material Effectivity MATERIAL EFFECTIVITY UPDATED

MATERIAL SET UPDATED

MATERIAL SET QUANTITY UPDATED

R

MATERIAL EFFECTIVITY UPDATED

MATERIAL SET UPDATED

MATERIAL SET QUANTITY UPDATED

R

MATERIAL EFFECTIVITY UPDATED

MATERIAL SET UPDATED

MATERIAL SET QUANTITY UPDATED

R

MATERIAL EFFECTIVITY UPDATED

MATERIAL SET UPDATED

MATERIAL SET QUANTITY UPDATED

R

MATERIAL EFFECTIVITY UPDATED

MATERIAL SET UPDATED

MATERIAL SET QUANTITY 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

LIST OF COMPONENTS

Kit 364033A01R02 PART MATERIAL SET UPDATED

MATERIAL SET LABEL UPDATED

QUANTITY UPDATED

PART NUMBER UPDATED

R

Kit 364033D01R02 PART MATERIAL SET UPDATED

MATERIAL SET LABEL UPDATED

QUANTITY UPDATED

ITEM NUMBER UPDATED

PART NUMBER UPDATED

KEYWORD UPDATED

R

Kit 364033D02R04 PART MATERIAL SET UPDATED

MATERIAL SET LABEL UPDATED

QUANTITY UPDATED

ITEM NUMBER UPDATED

PART NUMBER UPDATED

KEYWORD UPDATED

R

Kit 364033D10R01 PART MATERIAL SET UPDATED

MATERIAL SET LABEL UPDATED

QUANTITY UPDATED

ITEM NUMBER UPDATED

PART NUMBER UPDATED

KEYWORD UPDATED

R

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 2

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

Kit 364033D11R01 PART MATERIAL SET UPDATED

MATERIAL SET LABEL UPDATED

QUANTITY UPDATED

ITEM NUMBER UPDATED

PART NUMBER UPDATED

KEYWORD UPDATED

R

Kit 364033D12R01 PART MATERIAL SET UPDATED

MATERIAL SET LABEL UPDATED

QUANTITY UPDATED

ITEM NUMBER UPDATED

PART NUMBER UPDATED

KEYWORD UPDATED

R

Kit 364033D13R01 PART MATERIAL SET UPDATED

MATERIAL SET LABEL UPDATED

QUANTITY UPDATED

ITEM NUMBER UPDATED

PART NUMBER UPDATED

KEYWORD UPDATED

R

Kit 364033D14R01 PART MATERIAL SET UPDATED

MATERIAL SET LABEL UPDATED

QUANTITY UPDATED

ITEM NUMBER UPDATED

PART NUMBER UPDATED

KEYWORD UPDATED

R

Kit 364033D15R01 PART MATERIAL SET UPDATED

MATERIAL SET LABEL UPDATED

QUANTITY UPDATED

ITEM NUMBER UPDATED

PART NUMBER UPDATED

KEYWORD UPDATED

R

ACCOMPLISHMENT INSTRUCTIONS

TASK 364033- 831-848-001-Modification

Subtask 364033-831-001-001 SUBTASK SOLUTION UPDATED

PART NUMBER DESCRIPTION UPDATED

R

Subtask 364033-831-002-001 SUBTASK SOLUTION UPDATED

PART NUMBER DESCRIPTION UPDATED

R

Subtask 364033-831-003-001 SUBTASK SOLUTION UPDATED

PART NUMBER DESCRIPTION UPDATED

R

Subtask 364033-831-004-001 SUBTASK SOLUTION UPDATED

PART NUMBER DESCRIPTION UPDATED

R

Subtask 364033-831-006-001 SUBTASK SOLUTION UPDATED

MATERIAL LIST UPDATED

R

Subtask 364033-831-007-001 SUBTASK SOLUTION UPDATED

MATERIAL LIST UPDATED

R

Subtask 364033-831-008-001 SUBTASK SOLUTION UPDATED

MATERIAL LIST UPDATED

R

Subtask 364033-831-009-001 SUBTASK SOLUTION UPDATED

MATERIAL LIST UPDATED

R

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 3

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

Subtask 364033-831-010-001 SUBTASK SOLUTION UPDATED

QUANTITY UPDATED

PART NUMBER DESCRIPTION UPDATED

MATERIAL LIST UPDATED

R

Subtask 364033-831-011-001 SUBTASK SOLUTION UPDATED

PART NUMBER UPDATED

MATERIAL LIST UPDATED

R

Subtask 364033-831-012-001 SUBTASK SOLUTION UPDATED

PART NUMBER UPDATED

MATERIAL LIST UPDATED

R

Subtask 364033-831-013-001 SUBTASK SOLUTION UPDATED

MATERIAL LIST UPDATED

R

Subtask 364033-831-201-001 SUBTASK SOLUTION UPDATED

MATERIAL LIST UPDATED

R

Subtask 364033-831-202-001 SUBTASK SOLUTION UPDATED

MATERIAL LIST UPDATED

R

Subtask 364033-831-204-001 SUBTASK SOLUTION UPDATED

QUANTITY UPDATED

ITEM NUMBER UPDATED

PART NUMBER UPDATED

KEYWORD UPDATED

PART NUMBER DESCRIPTION UPDATED

MATERIAL LIST UPDATED

R

Subtask 364033-831-207-001 SUBTASK SOLUTION UPDATED

QUANTITY UPDATED

ITEM NUMBER UPDATED

PART NUMBER UPDATED

KEYWORD UPDATED

PART NUMBER DESCRIPTION UPDATED

MATERIAL LIST UPDATED

R

Subtask 364033-831-209-001 SUBTASK SOLUTION UPDATED

QUANTITY UPDATED

ITEM NUMBER UPDATED

PART NUMBER UPDATED

KEYWORD UPDATED

PART NUMBER DESCRIPTION UPDATED

MATERIAL LIST UPDATED

R

Subtask 364033-831-001-001 SUBTASK SOLUTION UPDATED

PART NUMBER DESCRIPTION UPDATED

R

Subtask 364033-831-002-001 SUBTASK SOLUTION UPDATED

PART NUMBER DESCRIPTION UPDATED

R

Subtask 364033-831-003-001 SUBTASK SOLUTION UPDATED

PART NUMBER DESCRIPTION UPDATED

R

Subtask 364033-831-004-001 SUBTASK SOLUTION UPDATED

PART NUMBER DESCRIPTION UPDATED

R

Subtask 364033-831-006-001 SUBTASK SOLUTION UPDATED

MATERIAL LIST UPDATED

R

Subtask 364033-831-007-001 SUBTASK SOLUTION UPDATED

MATERIAL LIST UPDATED

R

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 4

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Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

Subtask 364033-831-008-001 SUBTASK SOLUTION UPDATED

MATERIAL LIST UPDATED

R

Subtask 364033-831-009-001 SUBTASK SOLUTION UPDATED

MATERIAL LIST UPDATED

R

Subtask 364033-831-010-001 SUBTASK SOLUTION UPDATED

QUANTITY UPDATED

PART NUMBER DESCRIPTION UPDATED

MATERIAL LIST UPDATED

R

Subtask 364033-831-011-001 SUBTASK SOLUTION UPDATED

PART NUMBER UPDATED

MATERIAL LIST UPDATED

R

Subtask 364033-831-012-001 SUBTASK SOLUTION UPDATED

PART NUMBER UPDATED

MATERIAL LIST UPDATED

R

Subtask 364033-831-013-001 SUBTASK SOLUTION UPDATED

MATERIAL LIST UPDATED

R

Subtask 364033-831-201-003 SUBTASK SOLUTION UPDATED

MATERIAL LIST UPDATED

R

Subtask 364033-831-202-001 SUBTASK SOLUTION UPDATED

MATERIAL LIST UPDATED

R

Subtask 364033-831-204-001 SUBTASK SOLUTION UPDATED

QUANTITY UPDATED

ITEM NUMBER UPDATED

PART NUMBER UPDATED

KEYWORD UPDATED

PART NUMBER DESCRIPTION UPDATED

MATERIAL LIST UPDATED

R

Subtask 364033-831-207-002 SUBTASK SOLUTION UPDATED

QUANTITY UPDATED

ITEM NUMBER UPDATED

PART NUMBER UPDATED

KEYWORD UPDATED

PART NUMBER DESCRIPTION UPDATED

MATERIAL LIST UPDATED

R

Subtask 364033-831-209-001 SUBTASK SOLUTION UPDATED

QUANTITY UPDATED

ITEM NUMBER UPDATED

PART NUMBER UPDATED

KEYWORD UPDATED

PART NUMBER DESCRIPTION UPDATED

MATERIAL LIST UPDATED

R

Subtask 364033-831-001-001 SUBTASK SOLUTION UPDATED

PART NUMBER DESCRIPTION UPDATED

R

Subtask 364033-831-002-001 SUBTASK SOLUTION UPDATED

PART NUMBER DESCRIPTION UPDATED

R

Subtask 364033-831-003-001 SUBTASK SOLUTION UPDATED

PART NUMBER DESCRIPTION UPDATED

R

Subtask 364033-831-004-001 SUBTASK SOLUTION UPDATED

PART NUMBER DESCRIPTION UPDATED

R

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 5

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

Subtask 364033-831-006-001 SUBTASK SOLUTION UPDATED

MATERIAL LIST UPDATED

R

Subtask 364033-831-007-001 SUBTASK SOLUTION UPDATED

MATERIAL LIST UPDATED

R

Subtask 364033-831-008-001 SUBTASK SOLUTION UPDATED

MATERIAL LIST UPDATED

R

Subtask 364033-831-009-001 SUBTASK SOLUTION UPDATED

MATERIAL LIST UPDATED

R

Subtask 364033-831-010-001 SUBTASK SOLUTION UPDATED

QUANTITY UPDATED

PART NUMBER DESCRIPTION UPDATED

MATERIAL LIST UPDATED

R

Subtask 364033-831-011-001 SUBTASK SOLUTION UPDATED

PART NUMBER UPDATED

MATERIAL LIST UPDATED

R

Subtask 364033-831-012-001 SUBTASK SOLUTION UPDATED

PART NUMBER UPDATED

MATERIAL LIST UPDATED

R

Subtask 364033-831-013-001 SUBTASK SOLUTION UPDATED

MATERIAL LIST UPDATED

R

Subtask 364033-831-201-001 SUBTASK SOLUTION UPDATED

MATERIAL LIST UPDATED

R

Subtask 364033-831-202-001 SUBTASK SOLUTION UPDATED

MATERIAL LIST UPDATED

R

Subtask 364033-831-204-001 SUBTASK SOLUTION UPDATED

QUANTITY UPDATED

ITEM NUMBER UPDATED

PART NUMBER UPDATED

KEYWORD UPDATED

PART NUMBER DESCRIPTION UPDATED

MATERIAL LIST UPDATED

R

Subtask 364033-831-207-001 SUBTASK SOLUTION UPDATED

QUANTITY UPDATED

ITEM NUMBER UPDATED

PART NUMBER UPDATED

KEYWORD UPDATED

PART NUMBER DESCRIPTION UPDATED

MATERIAL LIST UPDATED

R

Subtask 364033-831-209-002 SUBTASK SOLUTION UPDATED

QUANTITY UPDATED

ITEM NUMBER UPDATED

PART NUMBER UPDATED

KEYWORD UPDATED

PART NUMBER DESCRIPTION UPDATED

MATERIAL LIST UPDATED

R

Subtask 364033-831-001-001 SUBTASK SOLUTION UPDATED

PART NUMBER DESCRIPTION UPDATED

R

Subtask 364033-831-002-001 SUBTASK SOLUTION UPDATED

PART NUMBER DESCRIPTION UPDATED

R

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 6

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Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

Subtask 364033-831-003-001 SUBTASK SOLUTION UPDATED

PART NUMBER DESCRIPTION UPDATED

R

Subtask 364033-831-004-001 SUBTASK SOLUTION UPDATED

PART NUMBER DESCRIPTION UPDATED

R

Subtask 364033-831-006-001 SUBTASK SOLUTION UPDATED

MATERIAL LIST UPDATED

R

Subtask 364033-831-007-001 SUBTASK SOLUTION UPDATED

MATERIAL LIST UPDATED

R

Subtask 364033-831-008-001 SUBTASK SOLUTION UPDATED

MATERIAL LIST UPDATED

R

Subtask 364033-831-009-001 SUBTASK SOLUTION UPDATED

MATERIAL LIST UPDATED

R

Subtask 364033-831-010-001 SUBTASK SOLUTION UPDATED

QUANTITY UPDATED

PART NUMBER DESCRIPTION UPDATED

MATERIAL LIST UPDATED

R

Subtask 364033-831-011-001 SUBTASK SOLUTION UPDATED

PART NUMBER UPDATED

MATERIAL LIST UPDATED

R

Subtask 364033-831-012-001 SUBTASK SOLUTION UPDATED

PART NUMBER UPDATED

MATERIAL LIST UPDATED

R

Subtask 364033-831-013-001 SUBTASK SOLUTION UPDATED

MATERIAL LIST UPDATED

R

Subtask 364033-831-201-001 SUBTASK SOLUTION UPDATED

MATERIAL LIST UPDATED

R

Subtask 364033-831-202-001 SUBTASK SOLUTION UPDATED

MATERIAL LIST UPDATED

R

Subtask 364033-831-204-001 SUBTASK SOLUTION UPDATED

QUANTITY UPDATED

ITEM NUMBER UPDATED

PART NUMBER UPDATED

KEYWORD UPDATED

PART NUMBER DESCRIPTION UPDATED

MATERIAL LIST UPDATED

R

Subtask 364033-831-207-002 SUBTASK SOLUTION UPDATED

QUANTITY UPDATED

ITEM NUMBER UPDATED

PART NUMBER UPDATED

KEYWORD UPDATED

PART NUMBER DESCRIPTION UPDATED

MATERIAL LIST UPDATED

R

Subtask 364033-831-209-002 SUBTASK SOLUTION UPDATED

QUANTITY UPDATED

ITEM NUMBER UPDATED

PART NUMBER UPDATED

KEYWORD UPDATED

PART NUMBER DESCRIPTION UPDATED

MATERIAL LIST UPDATED

R

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 7

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

Subtask 364033-831-001-001 SUBTASK SOLUTION UPDATED

PART NUMBER DESCRIPTION UPDATED

R

Subtask 364033-831-002-001 SUBTASK SOLUTION UPDATED

PART NUMBER DESCRIPTION UPDATED

R

Subtask 364033-831-003-001 SUBTASK SOLUTION UPDATED

PART NUMBER DESCRIPTION UPDATED

R

Subtask 364033-831-004-001 SUBTASK SOLUTION UPDATED

PART NUMBER DESCRIPTION UPDATED

R

Subtask 364033-831-006-001 SUBTASK SOLUTION UPDATED

MATERIAL LIST UPDATED

R

Subtask 364033-831-007-001 SUBTASK SOLUTION UPDATED

MATERIAL LIST UPDATED

R

Subtask 364033-831-008-001 SUBTASK SOLUTION UPDATED

MATERIAL LIST UPDATED

R

Subtask 364033-831-009-001 SUBTASK SOLUTION UPDATED

MATERIAL LIST UPDATED

R

Subtask 364033-831-010-001 SUBTASK SOLUTION UPDATED

QUANTITY UPDATED

PART NUMBER DESCRIPTION UPDATED

MATERIAL LIST UPDATED

R

Subtask 364033-831-011-001 SUBTASK SOLUTION UPDATED

PART NUMBER UPDATED

MATERIAL LIST UPDATED

R

Subtask 364033-831-012-001 SUBTASK SOLUTION UPDATED

PART NUMBER UPDATED

MATERIAL LIST UPDATED

R

Subtask 364033-831-013-001 SUBTASK SOLUTION UPDATED

MATERIAL LIST UPDATED

R

Subtask 364033-831-201-002 SUBTASK SOLUTION UPDATED

MATERIAL LIST UPDATED

R

Subtask 364033-831-202-002 SUBTASK SOLUTION UPDATED

MATERIAL LIST UPDATED

R

Subtask 364033-831-204-002 SUBTASK SOLUTION UPDATED

QUANTITY UPDATED

ITEM NUMBER UPDATED

PART NUMBER UPDATED

KEYWORD UPDATED

PART NUMBER DESCRIPTION UPDATED

MATERIAL LIST UPDATED

R

Subtask 364033-831-207-003 SUBTASK SOLUTION UPDATED

QUANTITY UPDATED

ITEM NUMBER UPDATED

PART NUMBER UPDATED

KEYWORD UPDATED

PART NUMBER DESCRIPTION UPDATED

MATERIAL LIST UPDATED

R

Subtask 364033-831-211-001 SUBTASK SOLUTION UPDATED

MATERIAL LIST UPDATED

R

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 8

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Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

Subtask 364033-831-209-003 SUBTASK SOLUTION UPDATED

QUANTITY UPDATED

ITEM NUMBER UPDATED

PART NUMBER UPDATED

KEYWORD UPDATED

PART NUMBER DESCRIPTION UPDATED

MATERIAL LIST UPDATED

R

Fig. A-FBCAA

Fig. A-FBCAA Sheet 01 SHEET UPDATED R

Fig. A-FBCAA Sheet 02 SHEET UPDATED R

Fig. A-FBNAA

Fig. A-FBNAA Sheet 01 SHEET UPDATED R

Fig. A-FBNAA Sheet 02 SHEET UPDATED R

Fig. A-FBNAA Sheet 03 SHEET UPDATED R

Fig. A-FBNAA Sheet 04 SHEET UPDATED R

Fig. A-FBNAA Sheet 05 SHEET UPDATED R

Fig. A-FBJAA

Fig. A-FBJAA Sheet 02 SHEET UPDATED R

Fig. A-FBJAA Sheet 03 SHEET UPDATED R

Fig. A-FBJAA Sheet 04 SHEET UPDATED R

Fig. A-FBMAA

Fig. A-FBMAA Sheet 01 SHEET UPDATED R

Fig. A-FBMAA Sheet 02 SHEET UPDATED R

Fig. A-FBMAA Sheet 03 SHEET UPDATED R

Fig. A-FBMAA Sheet 04 SHEET UPDATED R

Fig. A-FBMAA Sheet 05 SHEET UPDATED R

Fig. A-FBMAA Sheet 06 SHEET UPDATED R

Fig. A-FBMAA Sheet 08 SHEET UPDATED R

Fig. A-FBMAA Sheet 09 SHEET UPDATED R

Fig. A-FBMAA Sheet 11 SHEET UPDATED R

Fig. A-FBMAA Sheet 12 SHEET UPDATED R

Fig. A-FBMAA Sheet 13 SHEET UPDATED R

Fig. A-FBMAA Sheet 14 SHEET UPDATED R

Fig. A-FBMAA Sheet 15 SHEET UPDATED R

Fig. A-FBMAA Sheet 16 SHEET UPDATED R

Fig. A-FBMAA Sheet 17 SHEET UPDATED R

Fig. A-FBMAA Sheet 18 SHEET UPDATED R

Fig. A-FBMAA Sheet 19 SHEET UPDATED R

Fig. A-FBMAA Sheet 20 SHEET UPDATED R

Fig. A-FBMAA Sheet 21 SHEET UPDATED R

Fig. A-FBMAA Sheet 22 SHEET UPDATED R

Fig. A-FAAAA FIGURE SOLUTION ADDED N

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 9

6

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@A340

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

Fig. A-FAAAA Sheet 01 SHEET ADDED N

Fig. A-GBDAA

Fig. A-GBDAA Sheet 08 SHEET UPDATED R

Fig. A-GBDAE

Fig. A-GBDAE Sheet 07 SHEET UPDATED R

Fig. A-GBGAA

Fig. A-GBGAA Sheet 01 SHEET UPDATED R

Fig. A-GBGAA Sheet 02 SHEET UPDATED R

Fig. A-GBGAA Sheet 03 SHEET UPDATED R

Fig. A-GBGAA Sheet 04 SHEET UPDATED R

Fig. A-GBGAA Sheet 05 SHEET UPDATED R

Fig. A-GBGAA Sheet 06 SHEET UPDATED R

Fig. A-GBGAA Sheet 07 SHEET UPDATED R

Fig. A-GBGAA Sheet 08 SHEET UPDATED R

Fig. A-GBGAB

Fig. A-GBGAB Sheet 01 SHEET UPDATED R

Fig. A-GBGAB Sheet 02 SHEET UPDATED R

Fig. A-GBGAB Sheet 03 SHEET UPDATED R

Fig. A-GBGAB Sheet 04 SHEET UPDATED R

Fig. A-GBGAB Sheet 05 SHEET UPDATED R

Fig. A-GBGAB Sheet 06 SHEET UPDATED R

Fig. A-GBGAB Sheet 07 SHEET UPDATED R

Fig. A-GBGAB Sheet 08 SHEET UPDATED R

Fig. A-GBGAB Sheet 09 SHEET UPDATED R

Fig. A-GBGAE

Fig. A-GBGAE Sheet 01 SHEET UPDATED R

Fig. A-GBGAE Sheet 02 SHEET UPDATED R

Fig. A-GBGAE Sheet 03 SHEET UPDATED R

Fig. A-GBGAE Sheet 04 SHEET UPDATED R

Fig. A-GBGAE Sheet 05 SHEET UPDATED R

Fig. A-GBGAE Sheet 06 SHEET UPDATED R

Fig. A-GBGAE Sheet 07 SHEET UPDATED R

Fig. A-GBGAE Sheet 08 SHEET UPDATED R

Fig. A-GBGAE Sheet 09 SHEET UPDATED R

Fig. A-GBJAA

Fig. A-GBJAA Sheet 01 SHEET UPDATED R

Fig. A-GBJAA Sheet 02 SHEET UPDATED R

Fig. A-GBJAA Sheet 03 SHEET UPDATED R

Fig. A-GBJAA Sheet 04 SHEET UPDATED R

Fig. A-GBJAA Sheet 05 SHEET UPDATED R

Fig. A-GBJAA Sheet 06 SHEET UPDATED R

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 10

6

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@A340

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

Fig. A-GBJAA Sheet 07 SHEET UPDATED R

Fig. A-GBJAA Sheet 08 SHEET UPDATED R

Fig. A-GBJAC

Fig. A-GBJAC Sheet 01 SHEET UPDATED R

Fig. A-GBJAC Sheet 02 SHEET UPDATED R

Fig. A-GBJAC Sheet 03 SHEET UPDATED R

Fig. A-GBJAC Sheet 04 SHEET UPDATED R

Fig. A-GBJAC Sheet 05 SHEET UPDATED R

Fig. A-GBJAC Sheet 06 SHEET UPDATED R

Fig. A-GBJAC Sheet 07 SHEET UPDATED R

Fig. A-GBJAC Sheet 08 SHEET UPDATED R

Fig. A-GBJAE

Fig. A-GBJAE Sheet 01 SHEET UPDATED R

Fig. A-GBJAE Sheet 02 SHEET UPDATED R

Fig. A-GBJAE Sheet 04 SHEET UPDATED R

Fig. A-GBJAE Sheet 05 SHEET UPDATED R

Fig. A-GBJAE Sheet 06 SHEET UPDATED R

Fig. A-GBJAE Sheet 07 SHEET UPDATED R

Fig. A-GBJAE Sheet 08 SHEET UPDATED R

FILLING INSTRUCTIONS

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

Replace the complete document.

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

HISTORY OF PREVIOUS REVISIONS

No previous revision

REVISION SEQUENCE

ORIGINAL: Sep 23/11

REVISION No. : 01 - Jan 28/13

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 11

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@A340

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

This Page Intentionally Left Blank

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

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.

ATA SYSTEM: 36

TITLE: PNEUMATIC - LEAK DETECTION - INTRODUCE ADAPTED DUAL LOOP

OVERHEAT LEAK DETECTION APU BLEED AIR DUCT

**CONF ALL

MODIFICATIONS

MODIFICATION CLASSIFICATION

MAJOR None

MINOR 55198D46290 55198D46286 55961D46493 55962D46494 58529D46961

58530D46962

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

The Auxiliary Power Unit (APU) bleed leak detection system detects any ambient overheat in the

vicinity of the APU bleed air ducts. This system is made of a single overheat detection loop which runs

along the APU bleed air ducts in section 15/21 and sections 16 thru 19.1. The SFAR88 requirements

introduced Master Minimum Equipment List (MMEL) restrictions on this system.

This Service Bulletin details the installation of a second APU bleed leak detection loop (APU LOOP A)

in parallel to the current APU loop (which consequently becomes APU LOOP B) in section 15/21 and

sections 16 thru 19.1.

After installation of the second loop, the design and philosophy of the APU bleed leak detection system

will be similar to the wing bleed leak detection system (dual loop). This allows to dispatch the aircraft

with one loop inoperative for 800 FH.

The Operational/Maintenance Consequences of this Service Bulletin are covered by the update of the

affected publications detailed in ’PLANNING INFORMATION’.

GENERAL EVALUATION

EVALUATION TABLE

COMPLIANCE RECOMMENDED (1) CANCELS INSPECTION SB NO

POTENTIAL AD NO A/C OPERATION AFFECTED NO

RELIABILITY AFFECTED NO PAX COMFORT AFFECTED NO

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 1

6

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@A340

SERVICE BULLETIN

SUMMARY

EVALUATION TABLE

COST SAVING NO LROPS AFFECTED NO

STRUCTURAL LIFE EXTN NO VENDOR SB INVOLVED NO

NOTE (1): Service Bulletin recommended to be accomplished to prevent significant operational

disruptions.

MATERIAL PRICE INFORMATION

**CONF 001

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Kit 364033A01R02 1 28,600.00 Sensing element

Kit 364033A02R01 1 4,370.00 Bundle, Clamp, Hardware

Kit 364033D01R02 1 2,570.00 Electrical Equipment, Fitting, Protection

System, Clamp, Spacer, Strip, Splice,

Support, Placard Set, Cable Tie, Spring,

Tube and Attaching Parts

Kit 364033D03R00 1 106.00 Section and Attaching Parts

Kit 364033D10R01 1 13,750.00 Attaching Element, Sensing Element,

Sleeve, Spacer, Angle, Connector,

Clamp, Ring, Placard and Attaching

Parts

Kit 364033D13R01 1 10,070.00 Cable, Cable Tie, Attaching Element,

Sleeve, Spacer, Angle, Connector,

Clamp, Ring, Placard and Attaching

Parts

Kit 364033D16R00 1 3,780.00 Sleeve

TOTAL 63,246.00

**CONF 002

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Kit 364033A01R02 1 28,600.00 Sensing element

Kit 364033A02R01 1 4,370.00 Bundle, Clamp, Hardware

Kit 364033D01R02 1 2,570.00 Electrical Equipment, Fitting, Protection

System, Clamp, Spacer, Strip, Splice,

Support, Placard Set, Cable Tie, Spring,

Tube and Attaching Parts

Kit 364033D03R00 1 106.00 Section and Attaching Parts

Kit 364033D11R01 1 15,540.00 Attaching Element, Sensing Element,

Sleeve, Spacer, Angle, Connector,

Clamp, Ring, Placard and Attaching

Parts

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 2

6

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@A340

SERVICE BULLETIN

SUMMARY

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Kit 364033D13R01 1 10,070.00 Cable, Cable Tie, Attaching Element,

Sleeve, Spacer, Angle, Connector,

Clamp, Ring, Placard and Attaching

Parts

Kit 364033D16R00 1 3,780.00 Sleeve

TOTAL 65,036.00

**CONF 003

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Kit 364033A01R02 1 28,600.00 Sensing element

Kit 364033A02R01 1 4,370.00 Bundle, Clamp, Hardware

Kit 364033D01R02 1 2,570.00 Electrical Equipment, Fitting, Protection

System, Clamp, Spacer, Strip, Splice,

Support, Placard Set, Cable Tie, Spring,

Tube and Attaching Parts

Kit 364033D03R00 1 106.00 Section and Attaching Parts

Kit 364033D10R01 1 13,750.00 Attaching Element, Sensing Element,

Sleeve, Spacer, Angle, Connector,

Clamp, Ring, Placard and Attaching

Parts

Kit 364033D14R01 1 7,790.00 Cable, Cable Tie, Attaching Element,

Sleeve, Spacer, Angle, Connector,

Clamp, Ring, Placard and Attaching

Parts

Kit 364033D17R00 1 3,720.00 Sleeve

TOTAL 60,906.00

**CONF 004

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Kit 364033A01R02 1 28,600.00 Sensing element

Kit 364033A02R01 1 4,370.00 Bundle, Clamp, Hardware

Kit 364033D01R02 1 2,570.00 Electrical Equipment, Fitting, Protection

System, Clamp, Spacer, Strip, Splice,

Support, Placard Set, Cable Tie, Spring,

Tube and Attaching Parts

Kit 364033D03R00 1 106.00 Section and Attaching Parts

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 3

6

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@A340

SERVICE BULLETIN

SUMMARY

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Kit 364033D11R01 1 15,540.00 Attaching Element, Sensing Element,

Sleeve, Spacer, Angle, Connector,

Clamp, Ring, Placard and Attaching

Parts

Kit 364033D14R01 1 7,790.00 Cable, Cable Tie, Attaching Element,

Sleeve, Spacer, Angle, Connector,

Clamp, Ring, Placard and Attaching

Parts

Kit 364033D17R00 1 3,720.00 Sleeve

TOTAL 62,696.00

**CONF 005

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Kit 364033A01R02 1 28,600.00 Sensing element

Kit 364033A02R01 1 4,370.00 Bundle, Clamp, Hardware

Kit 364033D02R04 1 2,660.00 Fitting, Protection System, Clamp,

Spacer, Strip, Support, Spring, Cable

Tie, Placard Set, Electrical Equipment

and Attaching Parts

Kit 364033D03R00 1 106.00 Section and Attaching Parts

Kit 364033D12R01 1 15,540.00 Attaching Element, Sensing Element,

Sleeve, Spacer, Angle, Connector,

Clamp, Ring, Placard and Attaching

Parts

Kit 364033D15R01 1 8,010.00 Sensing Element, Bracket, Cable, Cable

Tie, Attaching Element, Sleeve, Spacer,

Angle, Connector, Clamp, Ring, Placard

and Attaching Parts

Kit 364033D17R00 1 3,720.00 Sleeve

TOTAL 63,006.00

EFFECTIVITY

**CONF ALL

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

47W 56W 83V AAW AFR AIB ALK ARG CAL CCA CES CPA DGA

DLH FIN GAF GFA HFY IBE IRC KAC KNE LAN M3R MAU MDG

MSR NMB PAL QAF RJA S3R SAA SAS SFB SLM SWR TAP THT

THY UAE VCV VIR XAX

The equivalent of this Service Bulletin has been validated on A330 aircraft MSN 0389.

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 4

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

SUMMARY

CONCURRENT REQUIREMENTS

Accomplishment of this Service Bulletin requires the prior or simultaneous accomplishment of the

following Service Bulletin(s) or the equivalent production modification(s):

Service Bulletin No. A340-31-4083 Mod. No. 52306S16981

53296S18162

A340-31-4111 55981S18827

A340-36-4028 51789S17829

NOTE: Make sure that either the Flight Warning Computer (FWC) L10 (Service Bulletin No.

A340-31-4083, Mod. No. 52306S16981, Mod. No. 53296S18162) or the FWC L10-1

(Service Bulletin No. A340-31-4111, Mod. No. 55981S18827 ) is embodied.

REFERENCES / REPERCUSSIONS

TFU None

OEB None

AOT None

SIL None

LINE MAINTENANCE AFFECTED No

LIFE LIMIT None

OTHER OIT SE 999.0063/06

OTHER O/REF SBIT-11-0009

NATURE OF THE WORK

AIRCRAFT YES

EQUIPMENT YES

HARD NO

SOFT NO

OBRM NO

MANPOWER

**CONF 001

Task 364033-831-848-001: Modification

TOTAL MANHOURS 268.75

ELAPSED TIME (HOURS) 144.0

**CONF 002

Task 364033-831-848-001: Modification

TOTAL MANHOURS 268.75

ELAPSED TIME (HOURS) 144.0

**CONF 003

Task 364033-831-848-001: Modification

TOTAL MANHOURS 268.75

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 5

6

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@A340

SERVICE BULLETIN

SUMMARY

Task 364033-831-848-001: Modification

ELAPSED TIME (HOURS) 144.0

**CONF 004

Task 364033-831-848-001: Modification

TOTAL MANHOURS 268.75

ELAPSED TIME (HOURS) 144.0

**CONF 005

Task 364033-831-848-001: Modification

TOTAL MANHOURS 273.00

ELAPSED TIME (HOURS) 144.0

APPENDICES

**CONF ALL

Appendix 01: Elapsed Time Assumptions

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 6

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@A340

SERVICE BULLETIN

SUMMARY

**CONF 001, 003

B

A

Z310

Z170

Z150 Z160

Z130

Z120

FR56

FR39.2

FR39.1

FR37

FR19

FR56

FR65

FR72

FR80

FR95

/82

FR101

800VU

A

B

SECOND SENSING

ELEMENT (APU LOOP B)

AND ASSOCIATED WIRING

Z140

F_SB_364033_6_SAAA_01_01

SECOND SENSING

ELEMENT (APU LOOP B)

AND ASSOCIATED WIRING

Figure A-GSAAA - Sheet 01

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 7

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@A340

SERVICE BULLETIN

SUMMARY

**CONF 002, 004 thru 005

B

A

Z310

Z170

Z150 Z160

Z130

Z120

FR56

FR39.2

FR39.1

FR19

FR56

FR65

FR72

FR80

FR95

/82

FR101

800VU

A

B

Z140

FR37.4

F_SB_364033_6_SAAB_01_01

SECOND SENSING

ELEMENT (APU LOOP B)

AND ASSOCIATED WIRING

SECOND SENSING

ELEMENT (APU LOOP B)

AND ASSOCIATED WIRING

Figure A-GSAAB - Sheet 01

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 8

6

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@A340

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

ATA SYSTEM: 36

TITLE: PNEUMATIC - LEAK DETECTION - INTRODUCE ADAPTED DUAL LOOP

OVERHEAT LEAK DETECTION APU BLEED AIR DUCT

MODIFICATION No.: 55198D46290 55198D46286 55961D46493 55962D46494 58529D46961

58530D46962

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

The equivalent of this Service Bulletin has been validated on A330 aircraft MSN 0389.

NOTE: The intent of this modification is achieved in production on MSN 0793 and

subsequent through modification Mod. No. 52260D44330.

(1) Models

340-211 340-212 340-213 340-311 340-312 340-313

(2) Effectivity by MSN

0002-0006 0009 0011 0013-0015 0018-0029 0031-0035 0038 0041 0043-0044

0046-0049 0051-0053 0056-0058 0061 0063 0074-0076 0078-0081 0084-0085

0088-0091 0093-0094 0101 0104 0114-0115 0117 0123 0125-0126 0128-0129 0131

0133-0137 0139 0141-0142 0145-0147 0149-0152 0154 0156-0161 0163-0164

0166-0170 0173-0176 0178-0180 0182 0185-0187 0190 0192-0194 0196-0197 0199

0201-0202 0204 0207-0208 0210 0212-0218 0220-0221 0225 0227-0228 0233

0235-0237 0239 0242-0243 0245-0246 0252 0257 0260 0263-0264 0268 0270

0273-0274 0278 0280 0282 0292 0297 0302 0304 0307 0310 0318-0319 0321 0325

0327 0329 0331-0332 0335 0347 0352 0354-0355 0359 0363 0367 0373-0374

0377-0379 0381 0385 0387 0390 0395 0399 0402 0406 0411 0413-0415 0424

0429-0430 0433-0435 0438 0442 0446-0447 0450 0459 0467 0470 0474 0483 0528

0538 0541 0544-0546 0554 0556 0559 0561-0562 0582 0585 0590 0598 0643 0646

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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@A340

SERVICE BULLETIN

0651 0668

(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

47W 0009

56W 0003 0011 0013 0015 0018 0019 0021

83V 0235 0239 0280 0292

AAW 0151

AFR 0029 0078 0084 0186 0207 0237 0245 0246 0260 0307 0310 0377

0399

AIB 0332

ALK 0032 0033 0034 0367 0374 0381

ARG 0048 0063 0074 0080 0085 0093 0094 0123 0126 0128 0373

CAL 0402 0406 0411 0415 0433 0541

CCA 0192 0199 0201 0242 0243 0264

CES 0129 0131 0141 0161 0182

CPA 0136 0137 0142 0147 0157 0160 0208 0218 0220 0227 0228

DGA 0075 0081

DLH 0020 0024 0027 0028 0035 0052 0053 0056 0135 0158 0213 0233

0252 0297 0304 0321 0325 0327 0335 0347 0352 0354 0379 0390

0434 0447

FIN 0058 0168 0174

GAF 0274 0355

GFA 0212 0215 0282 0554

HFY 0117 0133

IBE 0005 0088 0125 0134 0145 0146 0170 0193 0217 0221 0302 0318

0329 0387 0414 0459 0474 0483

IRC 0002

KAC 0089 0090 0101 0104

KNE 0004

LAN 0167 0359 0363 0429 0442

M3R 0061

MAU 0076 0152 0194 0268

MDG 0210 0319

MSR 0156 0159 0178

NMB 0047 0051

PAL 0173 0176 0187 0196

QAF 0026 0528

RJA 0014 0022 0038 0043

S3R 0204

SAA 0006 0197 0378 0544 0582 0590 0643 0646 0651

SAS 0413 0424 0430 0435 0450 0467 0470

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 2

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@A340

SERVICE BULLETIN

OPERATOR MSN

SFB 0046

SLM 0049

SWR 0150 0154 0169 0175 0179 0263 0538 0545 0546 0556 0559 0561

0562 0585 0598

TAP 0041 0044 0079 0091

THT 0385 0395 0438 0446 0668

THY 0023 0025 0057 0115 0180 0216 0257 0270 0331

UAE 0139 0149 0163 0166 0185 0190 0202 0236

VCV 0031

VIR 0114 0164 0214 0225

XAX 0273 0278

(4) Configuration by MSN

MSN CONFIGURATION

0002 0003 0005 0013 0015 0020 0023 0024 0025 0027 0028

0029 0032 0033 0034 0035 0041 0044 0047 0048 0049 0051

0052 0053 0056 0057 0058 0076 0078 0079 0084 0088 0089

0090 0091 0093 0094 0101 0104 0114 0115 0117 0123 0125

0126 0128 0129 0131 0133 0134 0135 0136 0137 0139 0141

0142 0145 0146 0147 0149 0150 0152 0154 0157 0158 0160

0161 0163 0164 0166 0167 0168 0169 0170 0173 0174 0175

0176 0179 0180 0182 0185 0186 0187 0190 0192 0193 0194

002

0004 0006 0009 0011 0014 0018 0019 0021 0022 0026 0031

0038 0043 0046 0061 0063 0074 0075 0080 0081 0085 0151

0156 0159 0178

001

0196 0197 0199 0201 0202 0207 0208 0210 0212 0213 0214

0215 0216 0217 0218 0220 0221 0225 0227 0228 0233 0235

0236 0237 0239 0242 0243 0245 0246 0252 0257 0260 0263

0264 0268 0270 0273 0274 0278 0280 0282 0292 0297 0302

0304 0307 0310 0318 0319 0321 0325 0327 0329 0331 0332

0335 0347 0352 0354 0355 0359 0363 0367 0373 0374 0377

0378 0379 0381 0385 0387 0390 0395 0399 0402 0406 0411

0413 0414 0415 0424 0429 0430 0433 0434 0435 0438 0442

0446 0447 0450 0459 0467 0470 0474 0483 0528 0538 0541

0545 0546 0554 0556 0559 0561 0562

004

0204 003

0544 0582 0585 0590 0598 0643 0646 0651 0668 005

(5) Configuration definition

**CONF 001

Config. 001 is valid for all A340-200 aircraft given in the effectivity of this Service Bulletin

without the Modification No. 44579D40539, Modification No. 48980D42587 and

Modification No.55961D46493.

**CONF 002

Config. 002 is valid for all A340-300 aircraft given in the effectivity of this Service Bulletin

without the Modification No. 44579D40539, Modification No. 48980D42587 and

Modification No.55961D46493.

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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@A340

SERVICE BULLETIN

**CONF 003

Config. 003 is valid for all A340-200 aircraft given in the effectivity of this Service Bulletin

on which the Modification No. 44579D40539 is embodied.

**CONF 004

Config. 004 is valid for all A340-300 aircraft given in the effectivity of this Service Bulletin

on which the Modification No. 44579D40539 is embodied.

**CONF 005

Config. 005 valid for all A340-300 aircraft given in the effectivity of this Service Bulletin

on which the Modification No. 44579D40539 and the Modification No. 48980D42587 are

embodied.

(6) Material Effectivity

**CONF 001

MATERIAL QTY PER A/C SEE NOTES

Kit 364033A01R02 1

Kit 364033A02R01 1

Kit 364033D01R02 1

Kit 364033D03R00 1

Kit 364033D10R01 1

Kit 364033D13R01 1

Kit 364033D16R00 1

Reidentified part set REIDA01 1

Consumable CMLD01 1

Consumable CMLA01 As required

**CONF 002

MATERIAL QTY PER A/C SEE NOTES

Kit 364033A01R02 1

Kit 364033A02R01 1

Kit 364033D01R02 1

Kit 364033D03R00 1

Kit 364033D11R01 1

Kit 364033D13R01 1

Kit 364033D16R00 1

Reidentified part set REIDA01 1

Consumable CMLD01 1

Consumable CMLA01 As required

**CONF 003

MATERIAL QTY PER A/C SEE NOTES

Kit 364033A01R02 1

Kit 364033A02R01 1

Kit 364033D01R02 1

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 4

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@A340

SERVICE BULLETIN

MATERIAL QTY PER A/C SEE NOTES

Kit 364033D03R00 1

Kit 364033D10R01 1

Kit 364033D14R01 1

Kit 364033D17R00 1

Reidentified part set REIDA01 1

Consumable CMLD01 1

Consumable CMLA01 As required

**CONF 004

MATERIAL QTY PER A/C SEE NOTES

Kit 364033A01R02 1

Kit 364033A02R01 1

Kit 364033D01R02 1

Kit 364033D03R00 1

Kit 364033D11R01 1

Kit 364033D14R01 1

Kit 364033D17R00 1

Reidentified part set REIDA01 1

Consumable CMLD01 1

Consumable CMLA01 As required

**CONF 005

MATERIAL QTY PER A/C SEE NOTES

Kit 364033A01R02 1

Kit 364033A02R01 1

Kit 364033D02R04 1

Kit 364033D03R00 1

Kit 364033D12R01 1

Kit 364033D15R01 1

Kit 364033D17R00 1

Reidentified part set REIDA01 1

Consumable CMLD01 1

Consumable CMLA01 As required

**CONF ALL

B. CONCURRENT REQUIREMENTS

Accomplishment of this Service Bulletin requires the prior or simultaneous accomplishment of

the following Service Bulletin(s) or the equivalent production modification(s):

Service Bulletin No. A340-31-4083 Mod. No. 52306S16981

53296S18162

A340-31-4111 55981S18827

A340-36-4028 51789S17829

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 5

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

NOTE: Make sure that either the Flight Warning Computer (FWC) L10 (Service

Bulletin No. A340-31-4083, Mod. No. 52306S16981, Mod. No. 53296S18162)

or the FWC L10-1 (Service Bulletin No. A340-31-4111, Mod. No.

55981S18827 ) is embodied.

C. REASON

(1) History

The Auxiliary Power Unit (APU) bleed leak detection system detects any ambient

overheat in the vicinity of the APU bleed air ducts. This system is made of a single

overheat detection loop which runs along the APU bleed air ducts in section 15/21 and

sections 16 thru 19.1. The SFAR88 requirements introduced Master Minimum Equipment

List (MMEL) restrictions on this system.

(2) Objective/Action

This Service Bulletin details the installation of a second APU bleed leak detection loop

(APU LOOP A) in parallel to the current APU loop (which consequently becomes APU

LOOP B) in section 15/21 and sections 16 thru 19.1.

(3) Advantages

After installation of the second loop, the design and philosophy of the APU bleed leak

detection system will be similar to the wing bleed leak detection system (dual loop). This

allows to dispatch the aircraft with one loop inoperative for 800 FH.

(4) Operational/Maintenance Consequences

The Operational/Maintenance Consequences of this Service Bulletin are covered by the

update of the affected publications detailed in ’PLANNING INFORMATION’.

D. DESCRIPTION

To accomplish this Service Bulletin it is necessary to :

**CONF 001

Task 364033-831-848-001: Modification

(1) Modify the Wiring between the Avionics Compartment and the Cargo Compartment.

(2) Modify the Wiring in the Main rack 800VU.

(3) Remove the sensing elements and the supports between FR39 and FR44.

(4) Remove the sensing elements and the supports between FR44 and FR51.

(5) Remove the sensing elements and the supports between FR51 and FR53.6.

(6) Remove the sensing elements and the supports between FR53.6 and FR55.

(7) If necessary, remove the ducts between FR53.5 and FR53.6 for access.

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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@A340

SERVICE BULLETIN

(8) Drill a new hole in the structure between FR53.5 and FR53.6.

(9) Install a new support for the routing of the sensing elements between FR53.5 and

FR53.6.

(10) If removed, install the ducts between FR53.5 and FR53.6.

(11) If necessary, remove the ducts between FR43 and FR45 for access.

(12) Replace the web assy and the half clamp assy at FR44.

(13) Install the new brackets for the routing of the sensing elements at FR44.

(14) If removed, install the ducts between FR43 and FR45.

(15) Install the sensing elements and the supports between FR39 and FR44.

(16) Install the sensing elements and the supports between FR44 and FR50.

(17) Install the sensing elements and the supports between FR50 and FR53.6.

(18) Install the sensing elements and the supports between FR53.6 and FR55.

(19) If necessary, remove the ducts between FR39 and FR40 for access.

(20) Install the new supports for the new harness between FR39.1 and FR39.2.

(21) Install the Interconnecting Electrical Wire FIN 309HF and 310HF, between the

sensing elements.

(22) Install the new Harness 2SG.

(23) Install the electrical wiring in the FWD cargo compartment

(24) Install the electrical wiring in the AFT cargo compartment and Bulk cargo

compartment

(25) Modify the electrical wiring in the AFT cargo compartment, Bulk cargo compartment

and Rear fuselage section

(26) Install an additional profile in the Rear fuselage section

(27) Install the electrical wiring in the rear fuselage section

(28) Remove the sensing elements in the AFT and Bulk cargo compartments

(29) Drill an additional hole for the dual loop overheat leak detection in the sheet metal

pressure bulkhead

(30) Install the sensing elements in the AFT and Bulk cargo compartments

(31) If removed, install the ducts between FR39 and FR40.

(32) Remove the sensing elements in the rear fuselage

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 7

6

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@A340

SERVICE BULLETIN

(33) Install the sensing elements in the rear fuselage

(34) Install the sleeves at the APU Bleed Air Duct

**CONF 002

Task 364033-831-848-001: Modification

(1) Modify the Wiring between the Avionics Compartment and the Cargo Compartment.

(2) Modify the Wiring in the Main rack 800VU.

(3) Remove the sensing elements and the supports between FR39 and FR44.

(4) Remove the sensing elements and the supports between FR44 and FR51.

(5) Remove the sensing elements and the supports between FR51 and FR53.6.

(6) Remove the sensing elements and the supports between FR53.6 and FR55.

(7) If necessary, remove the ducts between FR53.5 and FR53.6 for access.

(8) Drill a new hole in the structure between FR53.5 and FR53.6.

(9) Install a new support for the routing of the sensing elements between FR53.5 and

FR53.6.

(10) If removed, install the ducts between FR53.5 and FR53.6.

(11) If necessary, remove the ducts between FR43 and FR45 for access.

(12) Replace the web assy and the half clamp assy at FR44.

(13) Install the new brackets for the routing of the sensing elements at FR44.

(14) If removed, install the ducts between FR43 and FR45.

(15) Install the sensing elements and the supports between FR39 and FR44.

(16) Install the sensing elements and the supports between FR44 and FR50.

(17) Install the sensing elements and the supports between FR50 and FR53.6.

(18) Install the sensing elements and the supports between FR53.6 and FR55.

(19) If necessary, remove the ducts between FR39 and FR40 for access.

(20) Install the new supports for the new harness between FR39.1 and FR39.2.

(21) Install the Interconnecting Electrical Wire FIN 309HF and 310HF, between the

sensing elements.

(22) Install the new Harness 2SG.

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 8

6

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@A340

SERVICE BULLETIN

(23) Install the electrical wiring in the FWD cargo compartment

(24) Install the electrical wiring in the AFT cargo compartment and Bulk cargo

compartment

(25) Modify the electrical wiring in the AFT cargo compartment, Bulk cargo compartment

and Rear fuselage section

(26) Install an additional profile in the Rear fuselage section

(27) Install the electrical wiring in the rear fuselage section

(28) Remove the sensing elements in the AFT and Bulk cargo compartments

(29) Drill an additional hole for the dual loop overheat leak detection in the sheet metal

pressure bulkhead

(30) Install the sensing elements in the AFT and Bulk cargo compartments

(31) If removed, install the ducts between FR39 and FR40.

(32) Remove the sensing elements in the rear fuselage

(33) Install the sensing elements in the rear fuselage

(34) Install the sleeves at the APU Bleed Air Duct

**CONF 003

Task 364033-831-848-001: Modification

(1) Modify the Wiring between the Avionics Compartment and the Cargo Compartment.

(2) Modify the Wiring in the Main rack 800VU.

(3) Remove the sensing elements and the supports between FR39 and FR44.

(4) Remove the sensing elements and the supports between FR44 and FR51.

(5) Remove the sensing elements and the supports between FR51 and FR53.6.

(6) Remove the sensing elements and the supports between FR53.6 and FR55.

(7) If necessary, remove the ducts between FR53.5 and FR53.6 for access.

(8) Drill a new hole in the structure between FR53.5 and FR53.6.

(9) Install a new support for the routing of the sensing elements between FR53.5 and

FR53.6.

(10) If removed, install the ducts between FR53.5 and FR53.6.

(11) If necessary, remove the ducts between FR43 and FR45 for access.

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 9

6

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@A340

SERVICE BULLETIN

(12) Replace the web assy and the half clamp assy at FR44.

(13) Install the new brackets for the routing of the sensing elements at FR44.

(14) If removed, install the ducts between FR43 and FR45.

(15) Install the sensing elements and the supports between FR39 and FR44.

(16) Install the sensing elements and the supports between FR44 and FR50.

(17) Install the sensing elements and the supports between FR50 and FR53.6.

(18) Install the sensing elements and the supports between FR53.6 and FR55.

(19) If necessary, remove the ducts between FR39 and FR40 for access.

(20) Install the new supports for the new harness between FR39.1 and FR39.2.

(21) Install the Interconnecting Electrical Wire FIN 309HF and 310HF, between the

sensing elements.

(22) Install the new Harness 2SG.

(23) Install the electrical wiring in the FWD cargo compartment

(24) Install the electrical wiring in the AFT cargo compartment and Bulk cargo

compartment

(25) Modify the electrical wiring in the AFT cargo compartment, Bulk cargo compartment

and Rear fuselage section

(26) Install an additional profile in the Rear fuselage section

(27) Install the electrical wiring in the rear fuselage section

(28) Remove the sensing elements in the AFT and Bulk cargo compartments

(29) Drill an additional hole for the dual loop overheat leak detection in the sheet metal

pressure bulkhead

(30) Install the sensing elements in the AFT and Bulk cargo compartments

(31) If removed, install the ducts between FR39 and FR40.

(32) Remove the sensing elements in the rear fuselage

(33) Install the sensing elements in the rear fuselage

(34) Install the sleeves at the APU Bleed Air Duct

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 10

6

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@A340

SERVICE BULLETIN

**CONF 004

Task 364033-831-848-001: Modification

(1) Modify the Wiring between the Avionics Compartment and the Cargo Compartment.

(2) Modify the Wiring in the Main rack 800VU.

(3) Remove the sensing elements and the supports between FR39 and FR44.

(4) Remove the sensing elements and the supports between FR44 and FR51.

(5) Remove the sensing elements and the supports between FR51 and FR53.6.

(6) Remove the sensing elements and the supports between FR53.6 and FR55.

(7) If necessary, remove the ducts between FR53.5 and FR53.6 for access.

(8) Drill a new hole in the structure between FR53.5 and FR53.6.

(9) Install a new support for the routing of the sensing elements between FR53.5 and

FR53.6.

(10) If removed, install the ducts between FR53.5 and FR53.6.

(11) If necessary, remove the ducts between FR43 and FR45 for access.

(12) Replace the web assy and the half clamp assy at FR44.

(13) Install the new brackets for the routing of the sensing elements at FR44.

(14) If removed, install the ducts between FR43 and FR45.

(15) Install the sensing elements and the supports between FR39 and FR44.

(16) Install the sensing elements and the supports between FR44 and FR50.

(17) Install the sensing elements and the supports between FR50 and FR53.6.

(18) Install the sensing elements and the supports between FR53.6 and FR55.

(19) If necessary, remove the ducts between FR39 and FR40 for access.

(20) Install the new supports for the new harness between FR39.1 and FR39.2.

(21) Install the Interconnecting Electrical Wire FIN 309HF and 310HF, between the

sensing elements.

(22) Install the new Harness 2SG.

(23) Install the electrical wiring in the FWD cargo compartment

(24) Install the electrical wiring in the AFT cargo compartment and Bulk cargo

compartment

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 11

6

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@A340

SERVICE BULLETIN

(25) Modify the electrical wiring in the AFT cargo compartment, Bulk cargo compartment

and Rear fuselage section

(26) Install an additional profile in the Rear fuselage section

(27) Install the electrical wiring in the rear fuselage section

(28) Remove the sensing elements in the AFT and Bulk cargo compartments

(29) Drill an additional hole for the dual loop overheat leak detection in the sheet metal

pressure bulkhead

(30) Install the sensing elements in the AFT and Bulk cargo compartments

(31) If removed, install the ducts between FR39 and FR40.

(32) Remove the sensing elements in the rear fuselage

(33) Install the sensing elements in the rear fuselage

(34) Install the sleeves at the APU Bleed Air Duct

**CONF 005

Task 364033-831-848-001: Modification

(1) Modify the Wiring between the Avionics Compartment and the Cargo Compartment.

(2) Modify the Wiring in the Main rack 800VU.

(3) Remove the sensing elements and the supports between FR39 and FR44.

(4) Remove the sensing elements and the supports between FR44 and FR51.

(5) Remove the sensing elements and the supports between FR51 and FR53.6.

(6) Remove the sensing elements and the supports between FR53.6 and FR55.

(7) If necessary, remove the ducts between FR53.5 and FR53.6 for access.

(8) Drill a new hole in the structure between FR53.5 and FR53.6.

(9) Install a new support for the routing of the sensing elements between FR53.5 and

FR53.6.

(10) If removed, install the ducts between FR53.5 and FR53.6.

(11) If necessary, remove the ducts between FR43 and FR45 for access.

(12) Replace the web assy and the half clamp assy at FR44.

(13) Install the new brackets for the routing of the sensing elements at FR44.

(14) If removed, install the ducts between FR43 and FR45.

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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

6

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@A340

SERVICE BULLETIN

(15) Install the sensing elements and the supports between FR39 and FR44.

(16) Install the sensing elements and the supports between FR44 and FR50.

(17) Install the sensing elements and the supports between FR50 and FR53.6.

(18) Install the sensing elements and the supports between FR53.6 and FR55.

(19) If necessary, remove the ducts between FR39 and FR40 for access.

(20) Install the new supports for the new harness between FR39.1 and FR39.2.

(21) Install the Interconnecting Electrical Wire FIN 309HF and 310HF, between the

sensing elements.

(22) Install the new Harness 2SG.

(23) Install the electrical wiring in the FWD cargo compartment

(24) Install the electrical wiring in the AFT cargo compartment and Bulk cargo

compartment

(25) Modify the electrical wiring in the AFT cargo compartment, Bulk cargo compartment

and Rear fuselage section

(26) Install an additional profile in the Rear fuselage section

(27) Install the electrical wiring in the rear fuselage section

(28) Remove the sensing elements in the AFT and Bulk cargo compartments

(29) Drill an additional hole for the dual loop overheat leak detection in the CFK pressure

bulkhead

(30) Install the sensing elements in the AFT and Bulk cargo compartments

(31) If removed, install the ducts between FR39 and FR40.

(32) Remove the sensing elements in the rear fuselage

(33) Remove the sensing element, FIN 149HF, previously installed with Service Bulletin

No. A340-36-4028

(34) Install the sensing elements in the rear fuselage

(35) Install the sleeves at the APU Bleed Air Duct

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 13

6

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@A340

SERVICE BULLETIN

**CONF ALL

E. COMPLIANCE

(1) Classification

RECOMMENDED: Service Bulletin recommended to be accomplished to prevent

significant operational disruptions.

(2) Accomplishment Timescale

Accomplishment of this Service Bulletin is recommended at the earliest opportunity

where manpower and facilities are available.

F. APPROVAL

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

**CONF 001

Task 364033-831-848-001: Modification

Get Access 27.75

On Aircraft

Modify the Wiring between the Avionics Compartment

and the Cargo Compartment.

2.00

Modify the Wiring in the Main rack 800VU. 4.00

Remove the sensing elements and the supports

between FR39 and FR44.

4.00

Remove the sensing elements and the supports

between FR44 and FR51.

4.00

Remove the sensing elements and the supports

between FR51 and FR53.6.

4.00

Remove the sensing elements and the supports

between FR53.6 and FR55.

4.00

If necessary, remove the ducts between FR53.5 and

FR53.6 for access.

1.00

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 14

6

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@A340

SERVICE BULLETIN

Task 364033-831-848-001: Modification

Drill a new hole in the structure between FR53.5 and

FR53.6.

1.00

Install a new support for the routing of the sensing

elements between FR53.5 and FR53.6.

1.00

If removed, install the ducts between FR53.5 and

FR53.6.

2.00

If necessary, remove the ducts between FR43 and

FR45 for access.

1.00

Replace the web assy and the half clamp assy at

FR44.

3.00

Install the new brackets for the routing of the sensing

elements at FR44.

1.00

If removed, install the ducts between FR43 and FR45. 2.00

Install the sensing elements and the supports between

FR39 and FR44.

14.00

Install the sensing elements and the supports between

FR44 and FR50.

14.00

Install the sensing elements and the supports between

FR50 and FR53.6.

21.00

Install the sensing elements and the supports between

FR53.6 and FR55.

14.00

If necessary, remove the ducts between FR39 and

FR40 for access.

1.00

Install the new supports for the new harness between

FR39.1 and FR39.2.

3.00

Install the Interconnecting Electrical Wire FIN 309HF

and 310HF, between the sensing elements.

3.00

Install the new Harness 2SG. 26.00

Install the electrical wiring in the FWD cargo

compartment

7.50

Install the electrical wiring in the AFT cargo

compartment and Bulk cargo compartment

11.00

Modify the electrical wiring in the AFT cargo

compartment, Bulk cargo compartment and Rear

fuselage section

4.50

Install an additional profile in the Rear fuselage section 3.00

Install the electrical wiring in the rear fuselage section 14.00

Remove the sensing elements in the AFT and Bulk

cargo compartments

5.25

Drill an additional hole for the dual loop overheat leak

detection in the sheet metal pressure bulkhead

0.75

Install the sensing elements in the AFT and Bulk cargo

compartments

11.25

If removed, install the ducts between FR39 and FR40. 2.00

Remove the sensing elements in the rear fuselage 2.75

Install the sensing elements in the rear fuselage 5.75

Install the sleeves at the APU Bleed Air Duct 0.50

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 15

6

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@A340

SERVICE BULLETIN

Task 364033-831-848-001: Modification

Tests 5.00

Close-Up 37.75

TOTAL MANHOURS 268.75

ELAPSED TIME (HOURS) 144.0

**CONF 002

Task 364033-831-848-001: Modification

Get Access 27.75

On Aircraft

Modify the Wiring between the Avionics Compartment

and the Cargo Compartment.

2.00

Modify the Wiring in the Main rack 800VU. 4.00

Remove the sensing elements and the supports

between FR39 and FR44.

4.00

Remove the sensing elements and the supports

between FR44 and FR51.

4.00

Remove the sensing elements and the supports

between FR51 and FR53.6.

4.00

Remove the sensing elements and the supports

between FR53.6 and FR55.

4.00

If necessary, remove the ducts between FR53.5 and

FR53.6 for access.

1.00

Drill a new hole in the structure between FR53.5 and

FR53.6.

1.00

Install a new support for the routing of the sensing

elements between FR53.5 and FR53.6.

1.00

If removed, install the ducts between FR53.5 and

FR53.6.

2.00

If necessary, remove the ducts between FR43 and

FR45 for access.

1.00

Replace the web assy and the half clamp assy at

FR44.

3.00

Install the new brackets for the routing of the sensing

elements at FR44.

1.00

If removed, install the ducts between FR43 and FR45. 2.00

Install the sensing elements and the supports between

FR39 and FR44.

14.00

Install the sensing elements and the supports between

FR44 and FR50.

14.00

Install the sensing elements and the supports between

FR50 and FR53.6.

21.00

Install the sensing elements and the supports between

FR53.6 and FR55.

14.00

If necessary, remove the ducts between FR39 and

FR40 for access.

1.00

Install the new supports for the new harness between

FR39.1 and FR39.2.

3.00

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 16

6

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@A340

SERVICE BULLETIN

Task 364033-831-848-001: Modification

Install the Interconnecting Electrical Wire FIN 309HF

and 310HF, between the sensing elements.

3.00

Install the new Harness 2SG. 26.00

Install the electrical wiring in the FWD cargo

compartment

7.50

Install the electrical wiring in the AFT cargo

compartment and Bulk cargo compartment

11.00

Modify the electrical wiring in the AFT cargo

compartment, Bulk cargo compartment and Rear

fuselage section

4.50

Install an additional profile in the Rear fuselage section 3.00

Install the electrical wiring in the rear fuselage section 14.00

Remove the sensing elements in the AFT and Bulk

cargo compartments

5.25

Drill an additional hole for the dual loop overheat leak

detection in the sheet metal pressure bulkhead

0.75

Install the sensing elements in the AFT and Bulk cargo

compartments

11.25

If removed, install the ducts between FR39 and FR40. 2.00

Remove the sensing elements in the rear fuselage 2.75

Install the sensing elements in the rear fuselage 5.75

Install the sleeves at the APU Bleed Air Duct 0.50

Tests 5.00

Close-Up 37.75

TOTAL MANHOURS 268.75

ELAPSED TIME (HOURS) 144.0

**CONF 003

Task 364033-831-848-001: Modification

Get Access 27.75

On Aircraft

Modify the Wiring between the Avionics Compartment

and the Cargo Compartment.

2.00

Modify the Wiring in the Main rack 800VU. 4.00

Remove the sensing elements and the supports

between FR39 and FR44.

4.00

Remove the sensing elements and the supports

between FR44 and FR51.

4.00

Remove the sensing elements and the supports

between FR51 and FR53.6.

4.00

Remove the sensing elements and the supports

between FR53.6 and FR55.

4.00

If necessary, remove the ducts between FR53.5 and

FR53.6 for access.

1.00

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 17

6

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@A340

SERVICE BULLETIN

Task 364033-831-848-001: Modification

Drill a new hole in the structure between FR53.5 and

FR53.6.

1.00

Install a new support for the routing of the sensing

elements between FR53.5 and FR53.6.

1.00

If removed, install the ducts between FR53.5 and

FR53.6.

2.00

If necessary, remove the ducts between FR43 and

FR45 for access.

1.00

Replace the web assy and the half clamp assy at

FR44.

3.00

Install the new brackets for the routing of the sensing

elements at FR44.

1.00

If removed, install the ducts between FR43 and FR45. 2.00

Install the sensing elements and the supports between

FR39 and FR44.

14.00

Install the sensing elements and the supports between

FR44 and FR50.

14.00

Install the sensing elements and the supports between

FR50 and FR53.6.

21.00

Install the sensing elements and the supports between

FR53.6 and FR55.

14.00

If necessary, remove the ducts between FR39 and

FR40 for access.

1.00

Install the new supports for the new harness between

FR39.1 and FR39.2.

3.00

Install the Interconnecting Electrical Wire FIN 309HF

and 310HF, between the sensing elements.

3.00

Install the new Harness 2SG. 26.00

Install the electrical wiring in the FWD cargo

compartment

7.50

Install the electrical wiring in the AFT cargo

compartment and Bulk cargo compartment

11.00

Modify the electrical wiring in the AFT cargo

compartment, Bulk cargo compartment and Rear

fuselage section

4.50

Install an additional profile in the Rear fuselage section 3.00

Install the electrical wiring in the rear fuselage section 14.00

Remove the sensing elements in the AFT and Bulk

cargo compartments

5.25

Drill an additional hole for the dual loop overheat leak

detection in the sheet metal pressure bulkhead

0.75

Install the sensing elements in the AFT and Bulk cargo

compartments

11.25

If removed, install the ducts between FR39 and FR40. 2.00

Remove the sensing elements in the rear fuselage 2.75

Install the sensing elements in the rear fuselage 5.75

Install the sleeves at the APU Bleed Air Duct 0.50

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 18

6

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@A340

SERVICE BULLETIN

Task 364033-831-848-001: Modification

Tests 5.00

Close-Up 37.75

TOTAL MANHOURS 268.75

ELAPSED TIME (HOURS) 144.0

**CONF 004

Task 364033-831-848-001: Modification

Get Access 27.75

On Aircraft

Modify the Wiring between the Avionics Compartment

and the Cargo Compartment.

2.00

Modify the Wiring in the Main rack 800VU. 4.00

Remove the sensing elements and the supports

between FR39 and FR44.

4.00

Remove the sensing elements and the supports

between FR44 and FR51.

4.00

Remove the sensing elements and the supports

between FR51 and FR53.6.

4.00

Remove the sensing elements and the supports

between FR53.6 and FR55.

4.00

If necessary, remove the ducts between FR53.5 and

FR53.6 for access.

1.00

Drill a new hole in the structure between FR53.5 and

FR53.6.

1.00

Install a new support for the routing of the sensing

elements between FR53.5 and FR53.6.

1.00

If removed, install the ducts between FR53.5 and

FR53.6.

2.00

If necessary, remove the ducts between FR43 and

FR45 for access.

1.00

Replace the web assy and the half clamp assy at

FR44.

3.00

Install the new brackets for the routing of the sensing

elements at FR44.

1.00

If removed, install the ducts between FR43 and FR45. 2.00

Install the sensing elements and the supports between

FR39 and FR44.

14.00

Install the sensing elements and the supports between

FR44 and FR50.

14.00

Install the sensing elements and the supports between

FR50 and FR53.6.

21.00

Install the sensing elements and the supports between

FR53.6 and FR55.

14.00

If necessary, remove the ducts between FR39 and

FR40 for access.

1.00

Install the new supports for the new harness between

FR39.1 and FR39.2.

3.00

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 19

6

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@A340

SERVICE BULLETIN

Task 364033-831-848-001: Modification

Install the Interconnecting Electrical Wire FIN 309HF

and 310HF, between the sensing elements.

3.00

Install the new Harness 2SG. 26.00

Install the electrical wiring in the FWD cargo

compartment

7.50

Install the electrical wiring in the AFT cargo

compartment and Bulk cargo compartment

11.00

Modify the electrical wiring in the AFT cargo

compartment, Bulk cargo compartment and Rear

fuselage section

4.50

Install an additional profile in the Rear fuselage section 3.00

Install the electrical wiring in the rear fuselage section 14.00

Remove the sensing elements in the AFT and Bulk

cargo compartments

5.25

Drill an additional hole for the dual loop overheat leak

detection in the sheet metal pressure bulkhead

0.75

Install the sensing elements in the AFT and Bulk cargo

compartments

11.25

If removed, install the ducts between FR39 and FR40. 2.00

Remove the sensing elements in the rear fuselage 2.75

Install the sensing elements in the rear fuselage 5.75

Install the sleeves at the APU Bleed Air Duct 0.50

Tests 5.00

Close-Up 37.75

TOTAL MANHOURS 268.75

ELAPSED TIME (HOURS) 144.0

**CONF 005

Task 364033-831-848-001: Modification

Get Access 27.75

On Aircraft

Modify the Wiring between the Avionics Compartment

and the Cargo Compartment.

2.00

Modify the Wiring in the Main rack 800VU. 4.00

Remove the sensing elements and the supports

between FR39 and FR44.

4.00

Remove the sensing elements and the supports

between FR44 and FR51.

4.00

Remove the sensing elements and the supports

between FR51 and FR53.6.

4.00

Remove the sensing elements and the supports

between FR53.6 and FR55.

4.00

If necessary, remove the ducts between FR53.5 and

FR53.6 for access.

1.00

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 20

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@A340

SERVICE BULLETIN

Task 364033-831-848-001: Modification

Drill a new hole in the structure between FR53.5 and

FR53.6.

1.00

Install a new support for the routing of the sensing

elements between FR53.5 and FR53.6.

1.00

If removed, install the ducts between FR53.5 and

FR53.6.

2.00

If necessary, remove the ducts between FR43 and

FR45 for access.

1.00

Replace the web assy and the half clamp assy at

FR44.

3.00

Install the new brackets for the routing of the sensing

elements at FR44.

1.00

If removed, install the ducts between FR43 and FR45. 2.00

Install the sensing elements and the supports between

FR39 and FR44.

14.00

Install the sensing elements and the supports between

FR44 and FR50.

14.00

Install the sensing elements and the supports between

FR50 and FR53.6.

21.00

Install the sensing elements and the supports between

FR53.6 and FR55.

14.00

If necessary, remove the ducts between FR39 and

FR40 for access.

1.00

Install the new supports for the new harness between

FR39.1 and FR39.2.

3.00

Install the Interconnecting Electrical Wire FIN 309HF

and 310HF, between the sensing elements.

3.00

Install the new Harness 2SG. 26.00

Install the electrical wiring in the FWD cargo

compartment

7.50

Install the electrical wiring in the AFT cargo

compartment and Bulk cargo compartment

11.00

Modify the electrical wiring in the AFT cargo

compartment, Bulk cargo compartment and Rear

fuselage section

4.50

Install an additional profile in the Rear fuselage section 3.00

Install the electrical wiring in the rear fuselage section 14.00

Remove the sensing elements in the AFT and Bulk

cargo compartments

5.25

Drill an additional hole for the dual loop overheat leak

detection in the CFK pressure bulkhead

0.75

Install the sensing elements in the AFT and Bulk cargo

compartments

11.25

If removed, install the ducts between FR39 and FR40. 2.00

Remove the sensing elements in the rear fuselage 2.75

Remove the sensing element, FIN 149HF, previously

installed with Service Bulletin No. A340-36-4028

4.25

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 21

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SERVICE BULLETIN

Task 364033-831-848-001: Modification

Install the sensing elements in the rear fuselage 5.75

Install the sleeves at the APU Bleed Air Duct 0.50

Tests 5.00

Close-Up 37.75

TOTAL MANHOURS 273.00

ELAPSED TIME (HOURS) 144.0

**CONF ALL

H. WEIGHT AND BALANCE

**CONF 001

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 +8.315 KG (+18.3312 LB)

Effect on Balance +425.254 KGM (+3075.862 LB.FT )

**CONF 002

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 +8.470 KG (+18.6729 LB)

Effect on Balance +461.230 KGM (+3336.076 LB.FT )

**CONF 003

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 +6.722 KG (+14.8193 LB)

Effect on Balance +331.166 KGM (+2395.323 LB.FT )

**CONF 004

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 +6.877 KG (+15.1610 LB)

Effect on Balance +360.343 KGM (+2606.360 LB.FT )

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 22

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SERVICE BULLETIN

**CONF 005

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 +7.027 KG (+15.4917 LB)

Effect on Balance +369.588 KGM (+2673.230 LB.FT )

**CONF ALL

I. ELECTRICAL LOAD DATA

Not Changed

J. REFERENCES

**CONF 001

Aircraft Maintenance Manual (AMM) 06-20-00 06-31-53 06-41-52

06-41-53 11-00-00 12-34-24

20-21-15 21-20-00 21-26-00

22-96-00 22-97-00 24-41-00

25-21-41 25-28-41 25-52-00

25-53-00 25-54-00 25-75-41

31-50-00 31-60-00 32-12-00

33-13-00 33-14-00 36-11-34

36-12-00 36-12-41 36-22-00

36-22-17 52-10-00 52-30-00

52-33-00 52-52-00 53-00-00

53-35-11 53-35-13

ATA Common Support Data Dictionary (CSDD),

Chapter 2

Elec. Std. Practices Manual (ESPM) 20-33-00 20-33-10 20-42-12

20-43-10 20-43-42 20-48-00

20-52-10 20-55-00

Process and Material Specification (PMS) Process and Material Specification

(PMS) 01-02-36

Process and Material Specification

(PMS) 01-07-06

Process and Material Specification

(PMS) 01-07-89

Standards Manual (SM)

Structural Repair Manual (SRM) 51-23-12 51-24-00 51-42-11

51-42-21 51-43-00 51-47-00

51-75-12

Weight and Balance Manual (WBM) Weight and Balance Manual

(WBM) Chapter 1-00-07

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 23

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@A340

SERVICE BULLETIN

**CONF 002

Aircraft Maintenance Manual (AMM) 06-20-00 06-31-53 06-41-52

06-41-53 11-00-00 12-34-24

20-21-15 21-20-00 21-26-00

22-96-00 22-97-00 24-41-00

25-21-41 25-28-41 25-52-00

25-53-00 25-54-00 25-75-41

31-50-00 31-60-00 32-12-00

33-13-00 33-14-00 36-11-34

36-12-00 36-12-41 36-22-00

36-22-17 52-10-00 52-30-00

52-33-00 52-52-00 53-00-00

53-35-11 53-35-13

ATA Common Support Data Dictionary (CSDD),

Chapter 2

Elec. Std. Practices Manual (ESPM) 20-33-00 20-33-10 20-42-12

20-43-10 20-43-42 20-48-00

20-52-10 20-55-00

Process and Material Specification (PMS) Process and Material Specification

(PMS) 01-02-36

Process and Material Specification

(PMS) 01-07-06

Process and Material Specification

(PMS) 01-07-89

Standards Manual (SM)

Structural Repair Manual (SRM) 51-23-12 51-24-00 51-42-11

51-42-21 51-43-00 51-47-00

51-75-12

Weight and Balance Manual (WBM) Weight and Balance Manual

(WBM) Chapter 1-00-07

**CONF 003

Aircraft Maintenance Manual (AMM) 06-20-00 06-31-53 06-41-52

06-41-53 11-00-00 12-34-24

20-21-15 21-20-00 21-26-00

22-96-00 22-97-00 24-41-00

25-21-41 25-28-41 25-52-00

25-53-00 25-54-00 25-75-41

31-50-00 31-60-00 32-12-00

33-13-00 33-14-00 36-11-34

36-12-00 36-12-41 36-22-00

36-22-17 52-10-00 52-30-00

52-33-00 52-52-00 53-00-00

53-35-11 53-35-13

ATA Common Support Data Dictionary (CSDD),

Chapter 2

Elec. Std. Practices Manual (ESPM) 20-33-00 20-33-10 20-42-12

20-43-10 20-43-42 20-48-00

20-52-10 20-55-00

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 24

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@A340

SERVICE BULLETIN

Process and Material Specification (PMS) Process and Material Specification

(PMS) 01-02-36

Process and Material Specification

(PMS) 01-07-06

Process and Material Specification

(PMS) 01-07-89

Standards Manual (SM)

Structural Repair Manual (SRM) 51-23-12 51-24-00 51-42-11

51-42-21 51-43-00 51-47-00

51-75-12

Weight and Balance Manual (WBM) Weight and Balance Manual

(WBM) Chapter 1-00-07

**CONF 004

Aircraft Maintenance Manual (AMM) 06-20-00 06-31-53 06-41-52

06-41-53 11-00-00 12-34-24

20-21-15 21-20-00 21-26-00

22-96-00 22-97-00 24-41-00

25-21-41 25-28-41 25-52-00

25-53-00 25-54-00 25-75-41

31-50-00 31-60-00 32-12-00

33-13-00 33-14-00 36-11-34

36-12-00 36-12-41 36-22-00

36-22-17 52-10-00 52-30-00

52-33-00 52-52-00 53-00-00

53-35-11 53-35-13

ATA Common Support Data Dictionary (CSDD),

Chapter 2

Elec. Std. Practices Manual (ESPM) 20-33-00 20-33-10 20-42-12

20-43-10 20-43-42 20-48-00

20-52-10 20-55-00

Process and Material Specification (PMS) Process and Material Specification

(PMS) 01-02-36

Process and Material Specification

(PMS) 01-07-06

Process and Material Specification

(PMS) 01-07-89

Standards Manual (SM)

Structural Repair Manual (SRM) 51-23-12 51-24-00 51-42-11

51-42-21 51-43-00 51-47-00

51-75-12

Weight and Balance Manual (WBM) Weight and Balance Manual

(WBM) Chapter 1-00-07

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 25

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@A340

SERVICE BULLETIN

**CONF 005

Aircraft Maintenance Manual (AMM) 06-20-00 06-31-53 06-41-52

06-41-53 11-00-00 12-34-24

20-21-15 21-20-00 21-26-00

22-96-00 22-97-00 24-41-00

25-21-41 25-28-41 25-52-00

25-53-00 25-54-00 25-75-41

31-50-00 31-60-00 32-12-00

33-13-00 33-14-00 36-11-34

36-12-00 36-12-41 36-22-00

36-22-17 52-10-00 52-30-00

52-33-00 52-52-00 53-00-00

53-35-11 53-35-13

ATA Common Support Data Dictionary (CSDD),

Chapter 2

Elec. Std. Practices Manual (ESPM) 20-33-00 20-33-10 20-42-12

20-43-10 20-43-42 20-48-00

20-52-10 20-55-00

Process and Material Specification (PMS) Process and Material Specification

(PMS) 01-02-36

Process and Material Specification

(PMS) 01-07-06

Process and Material Specification

(PMS) 01-07-89

Standards Manual (SM)

Structural Repair Manual (SRM) 51-23-12 51-24-00 51-42-11

51-42-21 51-43-00 51-47-00

51-75-12

Weight and Balance Manual (WBM) Weight and Balance Manual

(WBM) Chapter 1-00-07

**CONF ALL

K. PUBLICATION AFFECTED

Aircraft Maintenance Manual (AMM) 36-12-00 36-22-00 36-22-17

Aircraft Schematic Manual (ASM) 36-22-00

Aircraft Wiring List (AWL)

Aircraft Wiring Manual (AWM) 36-12-04 36-22-05 91-03-06

91-03-07

Illustrated Parts Catalog (IPC) 24-92-02 24-92-04 24-92-32

25-14-01 25-71-01 25-92-31

36-12-04 36-22-03 36-22-04

53-36-03

Minimum Equipment List (MMEL)

Trouble Shooting Manual (TSM) 36-22-00

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:

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 26

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@A340

SERVICE BULLETIN

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

Sensing element 35605-2-255 35597-2-255 03 Not

Applicable

Sensing element 35610-2-255 35606-2-255 03 Not

Applicable

Sensing element 35624-2-255 35620-2-255 03 Not

Applicable

Sensing element 35612-2-255 35618-2-255 03 Not

Applicable

Sensing element 35600-2-255 35595-2-255 03 Not

Applicable

Sensing element 35571-2-255 35568-4-255 03 Not

Applicable

Sensing element 35580-2-255 35597-3-255 03 Not

Applicable

Sensing element 35611-3-255 35627-2-255 03 Not

Applicable

Blanket-Insulation F2581571700000 F0041196200000 03 Not

Applicable

Blanket-Insulation F2582261900000 F0041196200000 03 Not

Applicable

Blanket-Insulation F2581566600000 F0041196300000 03 Not

Applicable

Blanket-Insulation F2581666600000 F0041196400000 03 Not

Applicable

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 27

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@A340

SERVICE BULLETIN

DESCRIPTION OLD PART N ̊ NEW PART N ̊ INT MIXABILITY SEE

NOTES

Blanket-Insulation F2581677800000 F0041196500000 03 Not

Applicable

Blanket-Insulation F2581677900000 F0041196600000 03 Not

Applicable

Blanket-Insulation F2582242300000 F0041196700000 03 Not

Applicable

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

Common Support Data Dictionary (CSDD), Chapter 2.

**CONF 002

DESCRIPTION OLD PART N ̊ NEW PART N ̊ INT MIXABILITY SEE

NOTES

Sensing element 35605-2-255 35597-2-255 03 Not

Applicable

Sensing element 35610-2-255 35606-2-255 03 Not

Applicable

Sensing element 35624-2-255 35620-2-255 03 Not

Applicable

Sensing element 35612-2-255 35618-2-255 03 Not

Applicable

Sensing element 35600-2-255 35595-2-255 03 Not

Applicable

Sensing element 35571-2-255 35568-4-255 03 Not

Applicable

Sensing element 35580-2-255 35597-3-255 03 Not

Applicable

Sensing element 35611-3-255 35627-2-255 03 Not

Applicable

Blanket-Insulation F2581571700000 F0041196200000 03 Not

Applicable

Blanket-Insulation F2582261900000 F0041196200000 03 Not

Applicable

Blanket-Insulation F2581566600000 F0041196300000 03 Not

Applicable

Blanket-Insulation F2581666600000 F0041196400000 03 Not

Applicable

Blanket-Insulation F2581677800000 F0041196500000 03 Not

Applicable

Blanket-Insulation F2581677900000 F0041196600000 03 Not

Applicable

Blanket-Insulation F2582242300000 F0041196700000 03 Not

Applicable

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 28

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@A340

SERVICE BULLETIN

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

Common Support Data Dictionary (CSDD), Chapter 2.

**CONF 003

DESCRIPTION OLD PART N ̊ NEW PART N ̊ INT MIXABILITY SEE

NOTES

Sensing element 35605-2-255 35597-2-255 03 Not

Applicable

Sensing element 35610-2-255 35606-2-255 03 Not

Applicable

Sensing element 35624-2-255 35620-2-255 03 Not

Applicable

Sensing element 35612-2-255 35618-2-255 03 Not

Applicable

Sensing element 35600-2-255 35595-2-255 03 Not

Applicable

Sensing element 35571-2-255 35568-4-255 03 Not

Applicable

Sensing element 35580-2-255 35597-3-255 03 Not

Applicable

Sensing element 35611-3-255 35627-2-255 03 Not

Applicable

Blanket-Insulation F2581571700000 F0041196200000 03 Not

Applicable

Blanket-Insulation F2582261900000 F0041196200000 03 Not

Applicable

Blanket-Insulation F2581566600000 F0041196300000 03 Not

Applicable

Blanket-Insulation F2581666600000 F0041196400000 03 Not

Applicable

Blanket-Insulation F2581677800000 F0041196500000 03 Not

Applicable

Blanket-Insulation F2581677900000 F0041196600000 03 Not

Applicable

Blanket-Insulation F2582242300000 F0041196700000 03 Not

Applicable

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

Common Support Data Dictionary (CSDD), Chapter 2.

**CONF 004

DESCRIPTION OLD PART N ̊ NEW PART N ̊ INT MIXABILITY SEE

NOTES

Sensing element 35605-2-255 35597-2-255 03 Not

Applicable

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 29

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@A340

SERVICE BULLETIN

DESCRIPTION OLD PART N ̊ NEW PART N ̊ INT MIXABILITY SEE

NOTES

Sensing element 35610-2-255 35606-2-255 03 Not

Applicable

Sensing element 35624-2-255 35620-2-255 03 Not

Applicable

Sensing element 35612-2-255 35618-2-255 03 Not

Applicable

Sensing element 35600-2-255 35595-2-255 03 Not

Applicable

Sensing element 35571-2-255 35568-4-255 03 Not

Applicable

Sensing element 35580-2-255 35597-3-255 03 Not

Applicable

Sensing element 35611-3-255 35627-2-255 03 Not

Applicable

Blanket-Insulation F2581571700000 F0041196200000 03 Not

Applicable

Blanket-Insulation F2582261900000 F0041196200000 03 Not

Applicable

Blanket-Insulation F2581566600000 F0041196300000 03 Not

Applicable

Blanket-Insulation F2581666600000 F0041196400000 03 Not

Applicable

Blanket-Insulation F2581677800000 F0041196500000 03 Not

Applicable

Blanket-Insulation F2581677900000 F0041196600000 03 Not

Applicable

Blanket-Insulation F2582242300000 F0041196700000 03 Not

Applicable

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

Common Support Data Dictionary (CSDD), Chapter 2.

**CONF 005

DESCRIPTION OLD PART N ̊ NEW PART N ̊ INT MIXABILITY SEE

NOTES

Sensing element 35605-2-255 35597-2-255 03 Not

Applicable

Sensing element 35610-2-255 35606-2-255 03 Not

Applicable

Sensing element 35624-2-255 35620-2-255 03 Not

Applicable

Sensing element 35612-2-255 35618-2-255 03 Not

Applicable

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 30

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@A340

SERVICE BULLETIN

DESCRIPTION OLD PART N ̊ NEW PART N ̊ INT MIXABILITY SEE

NOTES

Sensing element 35600-2-255 35595-2-255 03 Not

Applicable

Sensing element 35571-2-255 35568-4-255 03 Not

Applicable

Sensing element 35580-2-255 35597-3-255 03 Not

Applicable

Sensing element 35611-3-255 35627-2-255 03 Not

Applicable

Blanket-Insulation F2581571700000 F0041196200000 03 Not

Applicable

Blanket-Insulation F2582261900000 F0041196200000 03 Not

Applicable

Blanket-Insulation F2581566600000 F0041196300000 03 Not

Applicable

Blanket-Insulation F2581666600000 F0041196400000 03 Not

Applicable

Blanket-Insulation F2581677800000 F0041196500000 03 Not

Applicable

Blanket-Insulation F2581677900000 F0041196600000 03 Not

Applicable

Blanket-Insulation F2582242300000 F0041196700000 03 Not

Applicable

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

Common Support Data Dictionary (CSDD), Chapter 2.

**CONF ALL

M. SPARES

None

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 31

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@A340

SERVICE BULLETIN

This Page Intentionally Left Blank

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 32

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SERVICE BULLETIN

2. MATERIAL INFORMATION

**CONF ALL

A. MATERIAL - PRICE AND AVAILABILITY

(1) Procurement Addresses

Kit 364033A01R02

Kit 364033A02R01

Kit 364033D01R02

Kit 364033D02R04

Kit 364033D03R00

Kit 364033D10R01

Kit 364033D11R01

Kit 364033D12R01

Kit 364033D13R01

Kit 364033D14R01

Kit 364033D15R01

Kit 364033D16R00

Kit 364033D17R00

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, Logistics and Suppliers

Weg beim Jaeger 150

D-22335 Hamburg

Germany

For ordering by internet:

http://spares.airbus.com

For ordering by fax:

+49 40 50 76 25 90

For ordering by E-mail:

airbus.kit@airbus.com

(2) Price and Availability

Kit 364033A01R02

Cost 28,600.00 USD

Availability 90 calendar days from receipt of order

The Kit availability given above is the standard lead time from the date of your purchase

order. If you require Kits before this time, please include a retrofit planning schedule with

your order so that we can try to comply with your requirements.

The sales terms (costs and availability) are estimated in relation to economic conditions

at the issue date of the Service Bulletin.

Kit 364033A02R01

Cost 4,370.00 USD

Availability 90 calendar days from receipt of order

The Kit availability given above is the standard lead time from the date of your purchase

order. If you require Kits before this time, please include a retrofit planning schedule with

your order so that we can try to comply with your requirements.

The sales terms (costs and availability) are estimated in relation to economic conditions

at the issue date of the Service Bulletin.

Kit 364033D01R02

Cost 2,570.00 USD

Availability 90 calendar days from receipt of order

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 33

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SERVICE BULLETIN

The Kit availability given above is the standard lead time from the date of your purchase

order. If you require Kits before this time, please include a retrofit planning schedule with

your order so that we can try to comply with your requirements.

The sales terms (costs and availability) are estimated in relation to economic conditions

at the issue date of the Service Bulletin.

Kit 364033D02R04

Cost 2,660.00 USD

Availability 90 calendar days from receipt of order

The Kit availability given above is the standard lead time from the date of your purchase

order. If you require Kits before this time, please include a retrofit planning schedule with

your order so that we can try to comply with your requirements.

The sales terms (costs and availability) are estimated in relation to economic conditions

at the issue date of the Service Bulletin.

Kit 364033D03R00

Cost 106.00 USD

Availability 90 calendar days from receipt of order

The Kit availability given above is the standard lead time from the date of your purchase

order. If you require Kits before this time, please include a retrofit planning schedule with

your order so that we can try to comply with your requirements.

The sales terms (costs and availability) are estimated in relation to economic conditions

at the issue date of the Service Bulletin.

Kit 364033D10R01

Cost 13,750.00 USD

Availability 90 calendar days from receipt of order

The Kit availability given above is the standard lead time from the date of your purchase

order. If you require Kits before this time, please include a retrofit planning schedule with

your order so that we can try to comply with your requirements.

The sales terms (costs and availability) are estimated in relation to economic conditions

at the issue date of the Service Bulletin.

Kit 364033D11R01

Cost 15,540.00 USD

Availability 90 calendar days from receipt of order

The Kit availability given above is the standard lead time from the date of your purchase

order. If you require Kits before this time, please include a retrofit planning schedule with

your order so that we can try to comply with your requirements.

The sales terms (costs and availability) are estimated in relation to economic conditions

at the issue date of the Service Bulletin.

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 34

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SERVICE BULLETIN

Kit 364033D12R01

Cost 15,540.00 USD

Availability 90 calendar days from receipt of order

The Kit availability given above is the standard lead time from the date of your purchase

order. If you require Kits before this time, please include a retrofit planning schedule with

your order so that we can try to comply with your requirements.

The sales terms (costs and availability) are estimated in relation to economic conditions

at the issue date of the Service Bulletin.

Kit 364033D13R01

Cost 10,070.00 USD

Availability 90 calendar days from receipt of order

The Kit availability given above is the standard lead time from the date of your purchase

order. If you require Kits before this time, please include a retrofit planning schedule with

your order so that we can try to comply with your requirements.

The sales terms (costs and availability) are estimated in relation to economic conditions

at the issue date of the Service Bulletin.

Kit 364033D14R01

Cost 7,790.00 USD

Availability 90 calendar days from receipt of order

The Kit availability given above is the standard lead time from the date of your purchase

order. If you require Kits before this time, please include a retrofit planning schedule with

your order so that we can try to comply with your requirements.

The sales terms (costs and availability) are estimated in relation to economic conditions

at the issue date of the Service Bulletin.

Kit 364033D15R01

Cost 8,010.00 USD

Availability 90 calendar days from receipt of order

The Kit availability given above is the standard lead time from the date of your purchase

order. If you require Kits before this time, please include a retrofit planning schedule with

your order so that we can try to comply with your requirements.

The sales terms (costs and availability) are estimated in relation to economic conditions

at the issue date of the Service Bulletin.

Kit 364033D16R00

Cost 3,780.00 USD

Availability 90 calendar days from receipt of order

The Kit availability given above is the standard lead time from the date of your purchase

order. If you require Kits before this time, please include a retrofit planning schedule with

your order so that we can try to comply with your requirements.

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 35

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SERVICE BULLETIN

The sales terms (costs and availability) are estimated in relation to economic conditions

at the issue date of the Service Bulletin.

Kit 364033D17R00

Cost 3,720.00 USD

Availability 90 calendar days from receipt of order

The Kit availability given above is the standard lead time from the date of your purchase

order. If you require Kits before this time, please include a retrofit planning schedule with

your order so that we can try to comply with your requirements.

The sales terms (costs and availability) are estimated in relation to economic conditions

at the issue date of the Service Bulletin.

B. INDUSTRY SUPPORT INFORMATION

As a special policy applied to this Service Bulletin, AIRBUS will provide a 15% reduction to

the applicable kits sales prices given in the paragraph Price and Availability for orders placed

before 31st December 2017.

C. LIST OF COMPONENTS

Kit 364033A01R02

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

NOTES

10 NSA5543-00 123 CLAMP

11 ASNA0342T04-01 16 BOLT

13 NSA5539S 249 SLEEVE

14 ASNA2397-10L 152 WASHER

15 NSA5542-00 20 NUT

16 NSA5527-03-01 41 SPACER

17 NSA5527-03-10 3 SPACER

18 NSA5527-03-11 15 SPACER

19 NAS6603-24 2 BOLT

20 NAS6603-1 73 BOLT

21 NAS6603-9 34 BOLT

22 NSA5527-03-15 1 SPACER

23 NAS6603-16 1 BOLT

24 NAS6603-15 7 BOLT

25 NSA5545-00 1 ANGLE

26 NAS6603-32 3 BOLT

28 NAS6603-12 1 BOLT

29 NAS6603-2 22 BOLT

30 NSA5546-00 7 ANGLE

32 F1131031621700 2 PLACARD

33 F1131031623700 2 PLACARD

34 F1131031621800 2 PLACARD

35 F1131031623800 2 PLACARD

36 F1131031623900 2 PLACARD

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 36

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@A340

SERVICE BULLETIN

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

NOTES

37 F1131031621900 2 PLACARD

38 F1131031624000 2 PLACARD

39 F1131031622000 2 PLACARD

40 F1131031622100 2 PLACARD

41 F1131031624100 2 PLACARD

42 F1131031622200 2 PLACARD

43 F1131031624200 2 PLACARD

44 F1131031620400 2 PLACARD

45 F1131031624300 2 PLACARD

63 ASNA2327-3-8 2 SUPPORT

64 F5391094700095 1 PLATE

65 NSA5456-3-8 1 SUPPORT

70 F3611548300000 3 SUPPORT

71 F3611548800000 1 SUPPORT

72 F3611548700000 1 SUPPORT

73 F3611548500000 1 SUPPORT

74 F3611548900000 1 SUPPORT

75 F3611548400000 1 SUPPORT

76 F3611548200000 1 SUPPORT

77 F3611548620000 1 SUPPORT

78 F3611549700000 1 SUPPORT

79 F3611549100000 9 SUPPORT

80 F3611549500000 1 SUPPORT

81 F3611549600000 1 SUPPORT

82 F3611549400000 1 SUPPORT

83 F3611549800000 1 SUPPORT

84 F3611549300000 1 SUPPORT

85 NSA5549-90 2 CONNECTR

86 NSA5538-00 3 CLAMP

87 NAS6603-17 5 BOLT

88 F1131031620500 1 PLACARD

89 F1131031624400 1 PLACARD

90 F1131031620600 1 PLACARD

91 F1131031624500 1 PLACARD

93 F3611549200095 1 SUPPORT

94 NAS6603-10 5 BOLT

95 F3611549000000 1 SUPPORT

96 F5392059300000 1 SUPPORT

97 ASNA2050DCJ3215 18 RIVET

98 F0041178800000 1 SUPPORT

99 F0041178800100 1 SUPPORT

100 35606-2-255 1 SNSGELEM (1) 35610-2-255 03

101 35621-2-255 1 SNSGELEM

102 35620-2-255 1 SNSGELEM (2) 35624-2-255 03

103 35618-2-255 2 SNSGELEM (3) 35612-2-255 03

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 37

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SERVICE BULLETIN

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

NOTES

104 35567-3-255 1 SNSGELEM

105 35598-2-255 1 SNSGELEM

106 35595-2-255 3 SNSGELEM (6) 35600-2-255 03

107 35596-2-255 1 SNSGELEM

108 35568-4-255 1 SNSGELEM (7) 35571-2-255 03

109 35597-3-255 1 SNSGELEM (8) 35580-2-255 03

110 35587-2-255 1 SNSGELEM

111 35627-2-255 1 SNSGELEM (9) 35611-3-255 03

112 35625-2-255 1 SNSGELEM

113 35610-2-255 1 SNSGELEM

114 35597-2-255 1 SNSGELEM (4) 35605-2-255 03

117 F5331591000200 1 WEB

118 F5331583500200 1 CLAMP

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

Common Support Data Dictionary (CSDD), Chapter 2.

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.

Kit 364033A02R01

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

NOTES

14 ASNA2397-10L 5 WASHER

16 NSA5527-03-01 2 SPACER

18 NSA5527-03-11 2 SPACER

22 NSA5527-03-15 1 SPACER

92 NSA57304-643ADL 1 PLATE

131 NSA935808-03 24 WASHER

134 NSA935807-16 1 CLAMP

135 NSA935807-20 1 CLAMP

141 NSA5527-03-02 3 SPACER

150 NSA935807-04 30 CLAMP

151 NSA5159-17 19 STUD

152 NSA5527-03-08 19 SPACER

153 NSA935808-01 13 WASHER

154 NSA5050-3 28 NUT

155 NSA5516-04ND 1 CLAMP

157 NSA5159-10 1 STUD

158 NAS1801-3-9 4 SCREW

159 NAS1801-3-8 2 SCREW

163 NSA5159-27 5 STUD

165 NSA5527-03-05 1 SPACER

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 38

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@A340

SERVICE BULLETIN

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

NOTES

166 NAS1801-3-12 4 SCREW

167 NAS1801-3-10 3 SCREW

168 NAS1801-3-22 1 SCREW

169 NSA935401-03 358 TIE

170 MS21042-3 4 NUT

171 NAS1801-3-17 2 SCREW

172 NAS1149F0332P 2 WASHER

173 NSA5527-03-12 6 SPACER

174 35301-74 2 CABLE

175 35301-75 2 CABLE 35301-74

176 NSA5516-21ND 5 CLAMP

177 NSA5516-22ND 5 CLAMP

178 NSA5516-23ND 5 CLAMP

179 NSA5516-07ND 2 CLAMP

180 NSA5516-08ND 2 CLAMP

181 NSA5516-10ND 2 CLAMP

182 NSA5050-4 1 NUT

183 NSA934710E20 3 SPRING

184 NSA934710T11 2 FITTING

E0432A04 20 (M) CONDUIT

F1131031521900 1 PLACARD

F1131031522000 1 PLACARD

F1131031522100 1 PLACARD

F9000095227895 1 BUNDLE

F9100095005595 1 PLACARD

NSA935401-06 50 TIE

NSA935401-08 300 TIE

NSA935401-13 350 TIE

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.

Kit 364033D01R02

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

NOTES

314 NAS1801-3-8 8 SCREW

320 NSA5527-03-02 5 SPACER

350 AS21919WCH13 6 CLAMP

351 MS21919WCH14 1 CLAMP

352 MS21919WCH8 1 CLAMP

353 NSA5067-3-1 1 NUT

400 F9297000500000 1 EQUIPMNT

402 F9237000207400 8 PLCRDSET

404 NSA935401-03 300 TIE

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 39

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@A340

SERVICE BULLETIN

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

NOTES

405 NSA935401-04 300 TIE

406 NSA935401-05 250 TIE

407 NSA935401-10 200 TIE

415 NSA934710T14 2 FITTING

416 NAS1801-3-9 8 SCREW

417 NAS1149C0332R 24 WASHER

418 NAS1149D0363K 4 WASHER

419 NAS1291C3M 10 NUT

420 NAS1102-3-10 4 SCREW

423 NAS1801-3-10 2 SCREW

430 NAS1100-04-6 4 SCREW

431 NAS1149CN416R 4 WASHER

432 MS21042-04 4 NUT

439 NSA5066-3-1 1 NUT

444 NAS1801-3-18 3 SCREW

448 NSA5066-3-2 1 NUT

449 NAS1801-08-8 2 SCREW

451 F9249016013200 1 PROTSYS

465 NAS1801-3-15 1 SCREW

469 ASNA0182-4ADL 2 STRIP

470 NAS1291C08M 3 NUT

471 NAS1149CN816R 5 WASHER

472 ASNA0182-3ADL 1 STRIP

475 NAS1801-08-36 2 SCREW

476 NSA5066-08-1 2 NUT

479 E0718-01 0.06 (ME) TUBING

480 NSA937210MB0300 0.1 (ME) TUBING

481 NSA936809RG0001 2 SPLICE

485 NSA934710E20 3 SPRING

488 E0126-06L 0.1 (ME) TUBING

489 F9249016510800 1 PROTSYS

492 ABS0580A17P 1 FITTING

493 NAS1801-3-21 2 SCREW

494 NSA935808C03 2 WASHER

496 NSA5527-03-08D 2 SPACER

501 NAS1801-3-27 2 SCREW

510 E0126-01L 0.35 (ME) TUBING

511 F9249016110900 1 PROTSYS

515 AS21919WCH07 1 CLAMP

517 ABS0513-09 1 SUPPORT

518 ABS0520-07P 1 NUT

521 AS21919WCH14 1 CLAMP

528 NAS1801-08-12 1 SCREW

536 AS21919WCH02 3 CLAMP

537 AS21919WCH09 1 CLAMP

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 40

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SERVICE BULLETIN

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

NOTES

843 MS21919WCH12 1 CLAMP

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.

Kit 364033D02R04

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

NOTES

314 NAS1801-3-8 8 SCREW

320 NSA5527-03-02 5 SPACER

350 AS21919WCH13 6 CLAMP

351 MS21919WCH14 1 CLAMP

352 MS21919WCH8 1 CLAMP

353 NSA5067-3-1 1 NUT

401 F9297000500200 1 EQUIPMNT

402 F9237000207400 9 PLCRDSET

404 NSA935401-03 300 TIE

405 NSA935401-04 300 TIE

406 NSA935401-05 250 TIE

407 NSA935401-10 200 TIE

415 NSA934710T14 2 FITTING

416 NAS1801-3-9 8 SCREW

417 NAS1149C0332R 32 WASHER

418 NAS1149D0363K 4 WASHER

419 NAS1291C3M 18 NUT

420 NAS1102-3-10 4 SCREW

423 NAS1801-3-10 2 SCREW

426 NAS6703U4 6 BOLT

427 NAS6703U5 2 BOLT

430 NAS1100-04-6 4 SCREW

431 NAS1149CN416R 4 WASHER

432 MS21042-04 4 NUT

439 NSA5066-3-1 1 NUT

444 NAS1801-3-18 3 SCREW

448 NSA5066-3-2 1 NUT

449 NAS1801-08-8 2 SCREW

451 F9249016013200 1 PROTSYS

465 NAS1801-3-15 1 SCREW

469 ASNA0182-4ADL 2 STRIP

470 NAS1291C08M 3 NUT

471 NAS1149CN816R 5 WASHER

472 ASNA0182-3ADL 1 STRIP

475 NAS1801-08-36 2 SCREW

476 NSA5066-08-1 2 NUT

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 41

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@A340

SERVICE BULLETIN

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

NOTES

479 E0718-01 0.12 (ME) TUBING

480 NSA937210MB0300 0.2 (ME) TUBING

481 NSA936809RG0001 4 SPLICE

485 NSA934710E20 3 SPRING

488 E0126-06L 0.1 (ME) TUBING

489 F9249016510800 1 PROTSYS

492 ABS0580A17P 1 FITTING

493 NAS1801-3-21 2 SCREW

494 NSA935808C03 2 WASHER

496 NSA5527-03-08D 2 SPACER

501 NAS1801-3-27 2 SCREW

510 E0126-01L 0.35 (ME) TUBING

511 F9249016110900 1 PROTSYS

515 AS21919WCH07 1 CLAMP

517 ABS0513-09 1 SUPPORT

518 ABS0520-07P 1 NUT

521 AS21919WCH14 1 CLAMP

528 NAS1801-08-12 1 SCREW

536 AS21919WCH02 3 CLAMP

537 AS21919WCH09 1 CLAMP

843 MS21919WCH12 1 CLAMP

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.

Kit 364033D03R00

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

NOTES

314 NAS1801-3-8 2 SCREW

460 F5397083308600 1 SECTION

461 MS21047L3 1 NUT

462 EN6101AD3-08 2 RIVET

463 NAS1149D0332J 2 WASHER

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.

Kit 364033D10R01

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

NOTES

57 D3627006026600 1 PLACARD

355 NSA5549-00 1 CONNECTR

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 42

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SERVICE BULLETIN

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

NOTES

356 F3627011520400 1 PLACARD

357 NSA5543-00 22 CLAMP

562 35602-2-255 2 ELEMENT

563 35600-2-255 2 SNSGELEM

564 35586-2-255 2 ELEMENT

566 35594-2-255 2 SNSGELEM

570 35604-2-255 2 SNSGELEM

572 35597-2-255 1 SNSGELEM

574 35599-3-255 1 ELEMENT

591 F3627011520600 1 PLACARD

592 NSA5546-00 6 ANGLE

593 F3627011522200 1 PLACARD

594 F3627011520800 2 PLACARD

596 A2117050220000 1 RING

597 NAS1149C0832R 1 WASHER

602 NSA5539S 152 SLEEVE

604 NAS1149C0863R 1 WASHER

606 F3627011520200 2 PLACARD

607 NAS1919C04S02U 12 RIVET

609 NSA5527-03-01 1 SPACER

610 NSA5538-00 2 CLAMP

611 F3627011521000 1 PLACARD

612 NSA5542-00 6 NUT

805 NAS1802-3-13 1 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.

Kit 364033D11R01

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

NOTES

57 D3627006026600 1 PLACARD

355 NSA5549-00 1 CONNECTR

356 F3627011520400 1 PLACARD

357 NSA5543-00 22 CLAMP

358 35587-2-255 2 SNSGELEM

389 F3627011520000 1 PLACARD

562 35602-2-255 2 ELEMENT

563 35600-2-255 2 SNSGELEM

564 35586-2-255 2 ELEMENT

566 35594-2-255 2 SNSGELEM

570 35604-2-255 2 SNSGELEM

572 35597-2-255 1 SNSGELEM

574 35599-3-255 1 ELEMENT

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 43

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@A340

SERVICE BULLETIN

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

NOTES

591 F3627011520600 1 PLACARD

592 NSA5546-00 7 ANGLE

593 F3627011522200 1 PLACARD

594 F3627011520800 2 PLACARD

596 A2117050220000 1 RING

597 NAS1149C0832R 1 WASHER

602 NSA5539S 176 SLEEVE

604 NAS1149C0863R 1 WASHER

606 F3627011520200 2 PLACARD

607 NAS1919C04S02U 14 RIVET

609 NSA5527-03-01 1 SPACER

610 NSA5538-00 2 CLAMP

611 F3627011521000 1 PLACARD

612 NSA5542-00 6 NUT

805 NAS1802-3-13 1 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.

Kit 364033D12R01

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

NOTES

57 D3627006026600 1 PLACARD

355 NSA5549-00 1 CONNECTR

356 F3627011520400 1 PLACARD

357 NSA5543-00 27 CLAMP

358 35587-2-255 2 SNSGELEM

389 F3627011520000 1 PLACARD

562 35602-2-255 2 ELEMENT

563 35600-2-255 2 SNSGELEM

564 35586-2-255 2 ELEMENT

566 35594-2-255 2 SNSGELEM

570 35604-2-255 2 SNSGELEM

572 35597-2-255 1 SNSGELEM

574 35599-3-255 1 ELEMENT

591 F3627011520600 1 PLACARD

592 NSA5546-00 7 ANGLE

593 F3627011522200 1 PLACARD

594 F3627011520800 2 PLACARD

596 A2117050220000 1 RING

597 NAS1149C0832R 1 WASHER

602 NSA5539S 176 SLEEVE

604 NAS1149C0863R 1 WASHER

606 F3627011520200 2 PLACARD

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 44

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@A340

SERVICE BULLETIN

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

NOTES

607 NAS1919C04S02U 14 RIVET

609 NSA5527-03-01 1 SPACER

610 NSA5538-00 2 CLAMP

611 F3627011521000 1 PLACARD

612 NSA5542-00 6 NUT

805 NAS1802-3-13 1 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.

Kit 364033D13R01

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

NOTES

59 NSA5545-00 3 ANGLE

313 NAS1801-3-19 2 SCREW

355 NSA5549-00 1 CONNECTR

357 NSA5543-00 40 CLAMP

360 35301-74 1 CABLE

361 35301-75 1 CABLE

364 35566-2-310 2 ELEMENT

366 35624-2-310 2 ELEMENT

371 35661-2-310 1 ELEMENT

372 AS21919WCH04 12 CLAMP

373 AS21919WCH10 2 CLAMP

374 F3617052620200 1 PLACARD

392 F3627011521400 1 PLACARD

393 F3627011521600 2 PLACARD

394 F3627011521800 2 PLACARD

398 35659-3-310 1 ELEMENT

405 NSA935401-04 2 TIE

416 NAS1801-3-9 5 SCREW

496 NSA5527-03-08D 2 SPACER

591 F3617052620000 1 PLACARD

596 A2117050220000 1 RING

597 NAS1149C0832R 1 WASHER

602 NSA5539S 104 SLEEVE

604 NAS1149C0863R 1 WASHER

607 NAS1919C04S02U 6 RIVET

608 D3627006026800 1 PLACARD

609 NSA5527-03-01 4 SPACER

610 NSA5538-00 4 CLAMP

612 NSA5542-00 3 NUT

640 MS21042-3 5 NUT

682 NAS1149D0332K 7 WASHER

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 45

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@A340

SERVICE BULLETIN

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

NOTES

805 NAS1802-3-13 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.

Kit 364033D14R01

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

NOTES

59 NSA5545-00 3 ANGLE

313 NAS1801-3-19 2 SCREW

314 NAS1801-3-8 2 SCREW

355 NSA5549-00 1 CONNECTR

357 NSA5543-00 37 CLAMP

360 35301-74 1 CABLE

361 35301-75 1 CABLE

362 35563-2-255 1 ELEMENT

363 35566-2-255 1 ELEMENT

365 35616-2-255 2 ELEMENT

369 35641-3-255 1 ELEMENT

370 35642-2-255 1 ELEMENT

372 AS21919WCH04 12 CLAMP

373 AS21919WCH10 2 CLAMP

374 F3617052620200 1 PLACARD

392 F3627011521400 1 PLACARD

393 F3627011521600 2 PLACARD

394 F3627011521800 2 PLACARD

397 NSA5527-03-04 2 SPACER

405 NSA935401-04 TIE

416 NAS1801-3-9 5 SCREW

496 NSA5527-03-08D 1 SPACER

591 F3617052620000 1 PLACARD

596 A2117050220000 1 RING

597 NAS1149C0832R 1 WASHER

602 NSA5539S 94 SLEEVE

604 NAS1149C0863R 1 WASHER

607 NAS1919C04S02U 6 RIVET

608 D3627006026800 1 PLACARD

609 NSA5527-03-01 3 SPACER

610 NSA5538-00 2 CLAMP

612 NSA5542-00 3 NUT

640 MS21042-3 5 NUT

682 NAS1149D0332K 7 WASHER

805 NAS1802-3-13 2 SCREW

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 46

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SERVICE BULLETIN

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.

Kit 364033D15R01

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

NOTES

59 NSA5545-00 3 ANGLE

313 NAS1801-3-19 2 SCREW

314 NAS1801-3-8 5 SCREW

355 NSA5549-00 1 CONNECTR

357 NSA5543-00 38 CLAMP

359 F3627014700200 1 BRACKET

360 35301-74 1 CABLE

361 35301-75 1 CABLE

362 35563-2-255 1 ELEMENT

363 35566-2-255 1 ELEMENT

365 35616-2-255 2 ELEMENT

367 35637-3-255 1 ELEMENT

368 35640-2-255 1 SNSGELEM

372 AS21919WCH04 12 CLAMP

373 AS21919WCH10 2 CLAMP

374 F3617052620200 1 PLACARD

392 F3627011521400 1 PLACARD

393 F3627011521600 2 PLACARD

394 F3627011521800 2 PLACARD

396 NAS1149F0332P 5 WASHER

397 NSA5527-03-04 2 SPACER

405 NSA935401-04 TIE

416 NAS1801-3-9 5 SCREW

496 NSA5527-03-08D SPACER

591 F3617052620000 1 PLACARD

596 A2117050220000 1 RING

597 NAS1149C0832R 1 WASHER

602 NSA5539S 92 SLEEVE

604 NAS1149C0863R 1 WASHER

607 NAS1919C04S02U 6 RIVET

608 D3627006026800 1 PLACARD

609 NSA5527-03-01 3 SPACER

610 NSA5538-00 2 CLAMP

612 NSA5542-00 3 NUT

640 MS21042-3 5 NUT

682 NAS1149D0332K 7 WASHER

805 NAS1802-3-13 2 SCREW

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 47

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SERVICE BULLETIN

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.

Kit 364033D16R00

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

NOTES

375 F3617062400000 1 SLEEVE

376 F3617062400200 1 SLEEVE

377 F3617062400400 1 SLEEVE

378 F3617062400600 1 SLEEVE

379 F3617062400800 1 SLEEVE

380 F3617062401000 1 SLEEVE

381 F3617062401200 1 SLEEVE

382 F3617062401400 1 SLEEVE

384 F3617062401800 1 SLEEVE

Kit 364033D17R00

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

NOTES

377 F3617062400400 1 SLEEVE

380 F3617062401600 1 SLEEVE

382 F3617062402200 1 SLEEVE

383 F3617062403200 1 SLEEVE

384 F3617062403400 1 SLEEVE

385 F3617062403600 1 SLEEVE

386 F3617062403800 1 SLEEVE

387 F3617062404000 1 SLEEVE

602 NSA5539S 6 SLEEVE

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.

D. LIST OF MATERIALS - OPERATOR SUPPLIED

(1) Consumable Materials

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO CML

MAT. No.

QTY PER A/C SEE

NOTES

Adhesive Tape (insulation Blanket

Repair)

08-073 As required

Interfay Sealant 09-005A As required

Corrosion Inhibiting Brush

Consistency

09-013B 0

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 48

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SERVICE BULLETIN

ITEM DESCRIPTION REFERENCE TO CML

MAT. No.

QTY PER A/C SEE

NOTES

Corrosion Inhibiting Fillet

Consistency

09-016B As required

Low Adhesion Polysulfide Sealant 09-019B As required

Solvent General Purpose 11-026 As required

Chemical Conversion Coating

Yellow Aluminum

13-002 As required

Anti-Corrosion Primer

(polyurethane)

16-001 As required

External Top Coat (polyurethane) 16-018 As required

Lint-Free Cotton Cloth 19-003 As required

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO CML

MAT. No.

QTY PER A/C SEE

NOTES

Adhesive Sealant 08-004 As required

Corrosion Inhibitive interfay Sealant 09-005 As required

Corrosion Inhibiting Brush

Consistency

09-013 As required

Corrosion Inhibiting, Fillet

Consistency

09-016 As required

Corrosion Inhibiting low Adhesion

Sealant

09-018 As required

Low Adhesion Polysulfide Sealant 09-019 As required

Chemical Conversion Coating

Yellow Aluminum

13-002 As required

Corrosion Preventive Temporary

Protective Compound

15-005 As required

Corrosion Preventive Temporary

Protective Compound

15-007 As required

Corrosion Preventive Temporary

Protective Compound

15-009 As required

Anti-Corrosion Primer

(polyurethane)

16-001 As required

Anti-Corrosion Primer (EpoxyImproved Adhesion)16-006 As required

External Top Coat (polyurethane) 16-018 As required

Wash Primer 16-020 As required

Lockwire, Stainless Steel, Annealed,

0.8mm Dia.

19-010 As required

Lockwire 0.6 Mm 19-018 As required

(2) Components

None

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 49

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SERVICE BULLETIN

(3) Equipment

None

E. PARTS TO BE RE-IDENTIFIED BY OPERATOR

Reidentified part set REIDA01

ITEM NEW PART N ̊ KEYWORD ITEM OLD PART N ̊ SEE

NOTES

F0041196200000 BLANKET F2581571700000

F2582261900000

F0041196300000 BLANKET F2581566600000

F0041196400000 BLANKET F2581666600000

F0041196500000 BLANKET F2581677800000

F0041196600000 BLANKET F2581677900000

F0041196700000 BLANKET F2582242300000

F. TOOLING

(1) Tooling - Price and Availability

None

(2) Tools

To accomplish this Service Bulletin it is necessary to use the tools listed in AMM

52-30-00, Page Block 201.

(3) Special Tools

None

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 50

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SERVICE BULLETIN

3. ACCOMPLISHMENT INSTRUCTIONS

Task 364033-831-848-001 - Modification

WARNING: MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND THE CAUTIONS

INCLUDED IN THE REFERENCED PROCEDURES.

WARNING: YOU MUST MAKE SURE THAT THE LANDING GEAR GROUND SAFETY

LOCKS ARE INSTALLED AND THE WHEEL CHOCKS ARE IN POSITION.

WARNING: MAKE SURE THAT THE SAFETY DEVICES AND THE WARNING NOTICES ARE

IN POSITION BEFORE YOU START A TASK ON OR NEAR:

- THE FLIGHT CONTROLS

- THE FLIGHT CONTROL SURFACES

- THE LANDING GEAR AND THE RELATED DOORS

- COMPONENTS THAT MOVE.

MOVEMENT OF COMPONENTS CAN KILL OR INJURE PERSONS.

WARNING: MAKE SURE THAT THE TRAVEL RANGES OF THE FLIGHT CONTROL

SURFACES ARE CLEAR BEFORE YOU PRESSURIZE/DEPRESSURIZE A

HYDRAULIC SYSTEM. AUTOMATIC MOVEMENT OF THE FLIGHT CONTROL

SURFACES CAN BE DANGEROUS AND/OR CAUSE DAMAGE.

WARNING: CLEANING SOLVENTS ARE FLAMMABLE, VOLATILE, TOXIC. THEY SHOULD

BE USED WITH ADEQUATE VENTILATION. AVOID PROLONGED BREATHING

OF VAPORS AND REPEATED OR PROLONGED CONTACT WITH THE SKIN,

OR CLOTHING.

WARNING: USE SOLVENTS/CLEANING AGENTS, SEALANTS AND OTHER SPECIAL

MATERIALS ONLY WITH A GOOD SUPPLY OF AIR THROUGH THE WORK

AREA.

THESE MATERIALS ARE POISONOUS, FLAMMABLE AND SKIN IRRITANTS.

OBEY THE MANUFACTURERS INSTRUCTIONS.

PUT ON PROTECTIVE CLOTHING.

DO NOT GET THEM IN YOUR MOUTH.

DO NOT SMOKE.

DO NOT BREATHE THE GAS.

GET MEDICAL HELP IF YOUR SKIN OR EYES BECOME IRRITATED.

CAUTION: MAKE SURE THAT THE MAINTENANCE DEVICES OF THE WING TIP BRAKES

ARE IN THE ’O’ (OPERATION) POSITION. THIS PREVENTS THE MOVEMENT

OF THE FLAP/SLAT TRANSMISSION SYSTEM DURING MAINTENANCE.

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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SERVICE BULLETIN

CAUTION: MAKE SURE THAT THE CLEANING AGENTS OR SOLVENTS DO NOT GET IN

OR ON:

- COMPONENT PARTS

- PROTECTIVE COVERS

- ELECTRICAL WIRING AND CONNECTORS.

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.

IF THERE IS CONTAMINATION (REFER TO ESPM 20-55-00).

Task Associated Data

**CONF 001

Zone

120 130 150 160 190 310

From 150 to 170

From 160 to 310

Modified FIN

23HF 24HF 25HF 27HF 28HF 29HF 30HF 31HF 32HF 33HF 34HF 97HF 98HF 99HF

100HF 101HF 102HF 137HF 139HF 140HF 301HF 302HF 303HF 304HF 305HF

306HF 307HF 308HF 309HF 310HF 311HF 312HF 358HF 359HF 360HF 361HF

5865VB 5866VB 5886VB 5215VC 5208VP 3503VS 3591VS 3593VS 5151VSA

5410VS

Access

Door 313AL 821 822 831

Manpower

TOTAL MANHOURS 268.75

ELAPSED TIME (HOURS) 144.0

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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SERVICE BULLETIN

**CONF 002

Zone

120 130 150 160 190 310

From 150 to 170

From 160 to 310

Modified FIN

23HF 24HF 25HF 26HF 27HF 28HF 29HF 30HF 31HF 32HF 33HF 34HF 97HF 98HF

99HF 100HF 101HF 102HF 137HF 139HF 140HF 301HF 302HF 303HF 304HF

305HF 306HF 307HF 308HF 309HF 310HF 311HF 312HF 358HF 359HF 360HF

361HF 5865VB 5866VB 5886VB 5215VC 5208VP 3503VS 3591VS 3593VS 5151VSA

5410VS

Access

Door 313AL 821 822 831

Manpower

TOTAL MANHOURS 268.75

ELAPSED TIME (HOURS) 144.0

**CONF 003

Zone

120 130 150 160 190 310

From 150 to 170

From 160 to 310

Modified FIN

23HF 24HF 25HF 27HF 28HF 29HF 30HF 31HF 32HF 33HF 34HF 97HF 98HF 99HF

100HF 101HF 102HF 137HF 139HF 140HF 301HF 302HF 303HF 304HF 305HF

306HF 307HF 308HF 309HF 310HF 311HF 312HF 358HF 359HF 360HF 361HF

5865VB 5866VB 5886VB 5215VC 5208VP 3503VS 3591VS 3593VS 5151VSA

5410VS

Access

Door 313AL 821 822 831

Manpower

TOTAL MANHOURS 268.75

ELAPSED TIME (HOURS) 144.0

**CONF 004

Zone

120 130 150 160 190 310

From 150 to 170

From 160 to 310

Modified FIN

23HF 24HF 25HF 26HF 27HF 28HF 29HF 30HF 31HF 32HF 33HF 34HF 97HF 98HF

99HF 100HF 101HF 102HF 137HF 139HF 140HF 301HF 302HF 303HF 304HF

305HF 306HF 307HF 308HF 309HF 310HF 311HF 312HF 358HF 359HF 360HF

361HF 5865VB 5866VB 5886VB 5215VC 5208VP 3503VS 3591VS 3593VS 5151VSA

5410VS

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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SERVICE BULLETIN

Access

Door 313AL 821 822 831

Manpower

TOTAL MANHOURS 268.75

ELAPSED TIME (HOURS) 144.0

**CONF 005

Zone

120 130 150 160 190 310

From 150 to 170

From 160 to 310

Modified FIN

23HF 24HF 25HF 26HF 27HF 28HF 29HF 30HF 31HF 32HF 33HF 34HF 97HF 98HF

99HF 100HF 101HF 102HF 137HF 139HF 140HF 149HF 150HF 151HF 301HF

302HF 303HF 304HF 305HF 306HF 307HF 308HF 309HF 310HF 311HF 312HF

358HF 359HF 360HF 361HF 5865VB 5866VB 5886VB 5215VC 5208VP 3503VS

3591VS 3593VS 5151VSA 5410VS 5865VSA 5865VSB

Access

Door 313AL 821 822 831

Manpower

TOTAL MANHOURS 273.00

ELAPSED TIME (HOURS) 144.0

**CONF ALL

A. GENERAL

**CONF 001

(1) Subtask 364033-910-201-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

Material necessary to do the job

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Adhesive Sealant 08-004 As required

Corrosion Inhibiting Brush

Consistency

09-013 As required

Corrosion Inhibiting, Fillet

Consistency

09-016 As required

Low Adhesion Polysulfide

Sealant

09-019 As required

Chemical Conversion

Coating Yellow Aluminum

13-002 As required

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 54

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SERVICE BULLETIN

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Corrosion Preventive

Temporary Protective

Compound

15-005 As required

Corrosion Preventive

Temporary Protective

Compound

15-007 As required

Corrosion Preventive

Temporary Protective

Compound

15-009 As required

Anti-Corrosion Primer

(polyurethane)

16-001 As required

Anti-Corrosion Primer

(Epoxy-Improved Adhesion)

16-006 As required

External Top Coat

(polyurethane)

16-018 As required

Wash Primer 16-020 As required

Lockwire, Stainless Steel,

Annealed, 0.8mm Dia.

19-010 As required

References

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

11-00-00, Page Block 001

Elec. Std. Practices Manual (ESPM) 20-33-10

20-42-12

Process and Material Specification

(PMS)

Process and Material Specification (PMS)

01-02-36

Process and Material Specification (PMS)

01-07-06

Process and Material Specification (PMS)

01-07-89

Standards Manual (SM)

Structural Repair Manual (SRM) 51-24-00

51-42-11

51-42-21

51-75-12

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

to the Consumable Materials List (CML)).

(b) For the identification of Zones (Refer to AMM 06-20-00, Page Block 001).

(c) For the application of low adhesion sealants (Refer to Process and Material

Specification (PMS) 01-02-36).

(d) Renew the protective finish (Refer to SRM 51-75-12).

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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(e) Apply:

Low Adhesion

Polysulfide Sealant

09-019 As required

to the interfaces of the structure and the mew parts.

(f) Fill gaps between the structure with:

Corrosion Inhibiting,

Fillet Consistency

09-016 As required

Low Adhesion

Polysulfide Sealant

09-019 As required

Adhesive Sealant 08-004 As required

(g) Protect the spot facing area with:

Chemical

Conversion Coating

Yellow Aluminum

13-002 As required

Anti-Corrosion

Primer

(polyurethane)

16-001 As required

External Top Coat

(polyurethane)

16-018 As required

(h) For the drilling of rivet holes:

- Use a soft lead pencil and make marks to show the position of the rivet holes.

- Make sure that you have the correct edge clearance before you drill the

fastener holes.

- If not shown otherwise the tolerance for rivet holes is + 0.1 mm (+ 0.004 in.).

- Transfer-drill the existing holes with a pilot drill and a drill bush.

- Deburr the holes after you have drilled them.

- Cut the rivets to the correct length, as necessary.

- When you remove fasteners you must be careful that you do not damage the

holes in the structure.

- Drill new fastener holes with a pilot drill of 2.5 mm (0.098 in.) diameter.

Increase the hole diameter to the correct size for the fastener which you must

install.

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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(i) Apply:

Wash Primer 16-020 As required

Anti-Corrosion

Primer (EpoxyImproved Adhesion)

16-006 As required

to the new drilled holes.

(j) Before riveting apply to all contact surfaces and components (Refer to SRM

51-24-00):

Corrosion Inhibiting

Brush Consistency

09-013 As required

(k) Install rivets immediately after you position the components with sealant. If not,

tacking pins must be installed temporarily in every third hole.

(l) After riveting, remove unwanted sealant from the work area and apply to the rivets:

Anti-Corrosion

Primer

(polyurethane)

16-001 As required

External Top Coat

(polyurethane)

16-018 As required

(m) Where locking facilities exist, make sure that the electrical connector is correctly

locked with:

Lockwire, Stainless

Steel, Annealed,

0.8mm Dia.

19-010 As required

(n) For the protective treatment in the upper area between Frame 80/82 thru Frame

91A, use:

Corrosion

Preventive

Temporary

Protective

Compound

15-005 As required

Corrosion

Preventive

Temporary

Protective

Compound

15-007 As required

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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SERVICE BULLETIN

Corrosion

Preventive

Temporary

Protective

Compound

15-009 As required

(o) For wiring and routing (Refer to ESPM 20-33-10).

(p) Do not fully tighten the attachment parts and ties until all the wire harnesses are

checked by a continuity test.

NOTE: To prevent chaffing, make sure that the cable harness does not sag

between the attachment points.

(q) Do not shrink the sleeves and shrinkable parts until you do a continuity test of the

new wires.

(r) For sleeve shrinking (Refer to ESPM 20-42-12).

(s) For the installation of sleeves and shrinkable parts (Refer to Process and Material

Specification (PMS) 01-07-06 and Process and Material Specification (PMS)

01-07-89).

(t) For fastener installation and removal (metallic structure) (Refer to SRM 51-42-11).

(u) For fastener installation and removal (composite structure) (Refer to SRM

51-42-21).

(v) For the installation of placards (Refer to AMM 11-00-00, Page Block 001).

(w) Install Service Bulletin identification placards at each end of new or modified

electrical wires in a position where they can be easily seen and at approximately

every 1.50 m (59.0 in.).

(2) Subtask 364033-910-001-001 - 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

Lint-Free Cotton Cloth 19-003 As required

References

Aircraft Maintenance Manual (AMM) 06-31-53, Page Block 001

06-41-53, Page Block 001

11-00-00, Page Block 201

Task 20-21-15-912-801

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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SERVICE BULLETIN

References

Elec. Std. Practices Manual (ESPM) 20-33-00

20-43-10

20-43-42

20-48-00

Standards Manual (SM)

Structural Repair Manual (SRM) 51-23-12

51-24-00

51-43-00

51-47-00

(a) Use a non metallic spatula to remove the sealant and clean the areas with :

Solvent General

Purpose

11-026 As required

(b) For fasteners spacing and margin (Refer to SRM 51-47-00).

(c) To torque tighten the electrical component fasteners (Refer to AMM Task

20-21-15-912-801).

(d) Clean the areas where you will install the placards with :

Solvent General

Purpose

11-026 As required

and

Lint-Free Cotton

Cloth

19-003 As required

(e) Apply the sealant (Refer to SRM 51-24-00).

(f) For the frames (FR) identification, (Refer to AMM 06-31-53, Page Block 001).

(g) For the identification of the access panels, (Refer to AMM 06-41-53, Page Block

001).

(h) Tag all the parts you must remove and retain to make the subsequent installation

easier.

(i) Put all the retained hardware in identified plastic bags and attach the bags to the

related unit.

(j) 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 the

Standards Manual (SM). The SM will give you the correct part number to part

number relationship.

(k) For the installation of the placards, (Refer to AMM 11-00-00, Page Block 201).

(l) Apply a special protection on new parts (Refer to SRM 51-23-12).

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(m) Obey the instructions for the general wiring installation, (Refer to ESPM 20-33-00).

(n) Obey the instructions of the pressure seals (Refer to ESPM 20-43-42).

(o) Obey the instructions of the splices installation (Refer to ESPM 20-43-10).

(p) Make sure that the electrical connectors are serviceable before you connect them

again.

(q) To install new wires, cut them to the necessary length, crimp the terminals and

connect them (Refer to ESPM 20-48-00).

(r) Put blanking plugs on the disconnected line ends.

(3) Subtask 364033-839-201-001 - 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 364033-910-201-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

Material necessary to do the job

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Adhesive Sealant 08-004 As required

Corrosion Inhibiting Brush

Consistency

09-013 As required

Corrosion Inhibiting, Fillet

Consistency

09-016 As required

Low Adhesion Polysulfide

Sealant

09-019 As required

Chemical Conversion

Coating Yellow Aluminum

13-002 As required

Corrosion Preventive

Temporary Protective

Compound

15-005 As required

Corrosion Preventive

Temporary Protective

Compound

15-007 As required

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 60

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SERVICE BULLETIN

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Corrosion Preventive

Temporary Protective

Compound

15-009 As required

Anti-Corrosion Primer

(polyurethane)

16-001 As required

Anti-Corrosion Primer

(Epoxy-Improved Adhesion)

16-006 As required

External Top Coat

(polyurethane)

16-018 As required

Wash Primer 16-020 As required

Lockwire, Stainless Steel,

Annealed, 0.8mm Dia.

19-010 As required

References

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

11-00-00, Page Block 001

Elec. Std. Practices Manual (ESPM) 20-33-10

20-42-12

Process and Material Specification

(PMS)

Process and Material Specification (PMS)

01-02-36

Process and Material Specification (PMS)

01-07-06

Process and Material Specification (PMS)

01-07-89

Standards Manual (SM)

Structural Repair Manual (SRM) 51-24-00

51-42-11

51-42-21

51-75-12

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

to the Consumable Materials List (CML)).

(b) For the identification of Zones (Refer to AMM 06-20-00, Page Block 001).

(c) For the application of low adhesion sealants (Refer to Process and Material

Specification (PMS) 01-02-36).

(d) Renew the protective finish (Refer to SRM 51-75-12).

(e) Apply:

Low Adhesion

Polysulfide Sealant

09-019 As required

to the interfaces of the structure and the mew parts.

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 61

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

(f) Fill gaps between the structure with:

Corrosion Inhibiting,

Fillet Consistency

09-016 As required

Low Adhesion

Polysulfide Sealant

09-019 As required

Adhesive Sealant 08-004 As required

(g) Protect the spot facing area with:

Chemical

Conversion Coating

Yellow Aluminum

13-002 As required

Anti-Corrosion

Primer

(polyurethane)

16-001 As required

External Top Coat

(polyurethane)

16-018 As required

(h) For the drilling of rivet holes:

- Use a soft lead pencil and make marks to show the position of the rivet holes.

- Make sure that you have the correct edge clearance before you drill the

fastener holes.

- If not shown otherwise the tolerance for rivet holes is + 0.1 mm (+ 0.004 in.).

- Transfer-drill the existing holes with a pilot drill and a drill bush.

- Deburr the holes after you have drilled them.

- Cut the rivets to the correct length, as necessary.

- When you remove fasteners you must be careful that you do not damage the

holes in the structure.

- Drill new fastener holes with a pilot drill of 2.5 mm (0.098 in.) diameter.

Increase the hole diameter to the correct size for the fastener which you must

install.

(i) Apply:

Wash Primer 16-020 As required

Anti-Corrosion

Primer (EpoxyImproved Adhesion)

16-006 As required

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 62

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

to the new drilled holes.

(j) Before riveting apply to all contact surfaces and components (Refer to SRM

51-24-00):

Corrosion Inhibiting

Brush Consistency

09-013 As required

(k) Install rivets immediately after you position the components with sealant. If not,

tacking pins must be installed temporarily in every third hole.

(l) After riveting, remove unwanted sealant from the work area and apply to the rivets:

Anti-Corrosion

Primer

(polyurethane)

16-001 As required

External Top Coat

(polyurethane)

16-018 As required

(m) Where locking facilities exist, make sure that the electrical connector is correctly

locked with:

Lockwire, Stainless

Steel, Annealed,

0.8mm Dia.

19-010 As required

(n) For the protective treatment in the upper area between Frame 80/82 thru Frame

91A, use:

Corrosion

Preventive

Temporary

Protective

Compound

15-005 As required

Corrosion

Preventive

Temporary

Protective

Compound

15-007 As required

Corrosion

Preventive

Temporary

Protective

Compound

15-009 As required

(o) For wiring and routing (Refer to ESPM 20-33-10).

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 63

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

(p) Do not fully tighten the attachment parts and ties until all the wire harnesses are

checked by a continuity test.

NOTE: To prevent chaffing, make sure that the cable harness does not sag

between the attachment points.

(q) Do not shrink the sleeves and shrinkable parts until you do a continuity test of the

new wires.

(r) For sleeve shrinking (Refer to ESPM 20-42-12).

(s) For the installation of sleeves and shrinkable parts (Refer to Process and Material

Specification (PMS) 01-07-06 and Process and Material Specification (PMS)

01-07-89).

(t) For fastener installation and removal (metallic structure) (Refer to SRM 51-42-11).

(u) For fastener installation and removal (composite structure) (Refer to SRM

51-42-21).

(v) For the installation of placards (Refer to AMM 11-00-00, Page Block 001).

(w) Install Service Bulletin identification placards at each end of new or modified

electrical wires in a position where they can be easily seen and at approximately

every 1.50 m (59.0 in.).

(2) Subtask 364033-910-001-001 - 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

Lint-Free Cotton Cloth 19-003 As required

References

Aircraft Maintenance Manual (AMM) 06-31-53, Page Block 001

06-41-53, Page Block 001

11-00-00, Page Block 201

Task 20-21-15-912-801

Elec. Std. Practices Manual (ESPM) 20-33-00

20-43-10

20-43-42

20-48-00

Standards Manual (SM)

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 64

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

References

Structural Repair Manual (SRM) 51-23-12

51-24-00

51-43-00

51-47-00

(a) Use a non metallic spatula to remove the sealant and clean the areas with :

Solvent General

Purpose

11-026 As required

(b) For fasteners spacing and margin (Refer to SRM 51-47-00).

(c) To torque tighten the electrical component fasteners (Refer to AMM Task

20-21-15-912-801).

(d) Clean the areas where you will install the placards with :

Solvent General

Purpose

11-026 As required

and

Lint-Free Cotton

Cloth

19-003 As required

(e) Apply the sealant (Refer to SRM 51-24-00).

(f) For the frames (FR) identification, (Refer to AMM 06-31-53, Page Block 001).

(g) For the identification of the access panels, (Refer to AMM 06-41-53, Page Block

001).

(h) Tag all the parts you must remove and retain to make the subsequent installation

easier.

(i) Put all the retained hardware in identified plastic bags and attach the bags to the

related unit.

(j) 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 the

Standards Manual (SM). The SM will give you the correct part number to part

number relationship.

(k) For the installation of the placards, (Refer to AMM 11-00-00, Page Block 201).

(l) Apply a special protection on new parts (Refer to SRM 51-23-12).

(m) Obey the instructions for the general wiring installation, (Refer to ESPM 20-33-00).

(n) Obey the instructions of the pressure seals (Refer to ESPM 20-43-42).

(o) Obey the instructions of the splices installation (Refer to ESPM 20-43-10).

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 65

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

(p) Make sure that the electrical connectors are serviceable before you connect them

again.

(q) To install new wires, cut them to the necessary length, crimp the terminals and

connect them (Refer to ESPM 20-48-00).

(r) Put blanking plugs on the disconnected line ends.

(3) Subtask 364033-839-201-001 - 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 003

(1) Subtask 364033-910-201-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

Material necessary to do the job

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Adhesive Sealant 08-004 As required

Corrosion Inhibiting Brush

Consistency

09-013 As required

Corrosion Inhibiting, Fillet

Consistency

09-016 As required

Low Adhesion Polysulfide

Sealant

09-019 As required

Chemical Conversion

Coating Yellow Aluminum

13-002 As required

Corrosion Preventive

Temporary Protective

Compound

15-005 As required

Corrosion Preventive

Temporary Protective

Compound

15-007 As required

Corrosion Preventive

Temporary Protective

Compound

15-009 As required

Anti-Corrosion Primer

(polyurethane)

16-001 As required

Anti-Corrosion Primer

(Epoxy-Improved Adhesion)

16-006 As required

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 66

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

External Top Coat

(polyurethane)

16-018 As required

Wash Primer 16-020 As required

Lockwire, Stainless Steel,

Annealed, 0.8mm Dia.

19-010 As required

References

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

11-00-00, Page Block 001

Elec. Std. Practices Manual (ESPM) 20-33-10

20-42-12

Process and Material Specification

(PMS)

Process and Material Specification (PMS)

01-02-36

Process and Material Specification (PMS)

01-07-06

Process and Material Specification (PMS)

01-07-89

Standards Manual (SM)

Structural Repair Manual (SRM) 51-24-00

51-42-11

51-42-21

51-75-12

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

to the Consumable Materials List (CML)).

(b) For the identification of Zones (Refer to AMM 06-20-00, Page Block 001).

(c) For the application of low adhesion sealants (Refer to Process and Material

Specification (PMS) 01-02-36).

(d) Renew the protective finish (Refer to SRM 51-75-12).

(e) Apply:

Low Adhesion

Polysulfide Sealant

09-019 As required

to the interfaces of the structure and the mew parts.

(f) Fill gaps between the structure with:

Corrosion Inhibiting,

Fillet Consistency

09-016 As required

Low Adhesion

Polysulfide Sealant

09-019 As required

Adhesive Sealant 08-004 As required

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 67

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

(g) Protect the spot facing area with:

Chemical

Conversion Coating

Yellow Aluminum

13-002 As required

Anti-Corrosion

Primer

(polyurethane)

16-001 As required

External Top Coat

(polyurethane)

16-018 As required

(h) For the drilling of rivet holes:

- Use a soft lead pencil and make marks to show the position of the rivet holes.

- Make sure that you have the correct edge clearance before you drill the

fastener holes.

- If not shown otherwise the tolerance for rivet holes is + 0.1 mm (+ 0.004 in.).

- Transfer-drill the existing holes with a pilot drill and a drill bush.

- Deburr the holes after you have drilled them.

- Cut the rivets to the correct length, as necessary.

- When you remove fasteners you must be careful that you do not damage the

holes in the structure.

- Drill new fastener holes with a pilot drill of 2.5 mm (0.098 in.) diameter.

Increase the hole diameter to the correct size for the fastener which you must

install.

(i) Apply:

Wash Primer 16-020 As required

Anti-Corrosion

Primer (EpoxyImproved Adhesion)

16-006 As required

to the new drilled holes.

(j) Before riveting apply to all contact surfaces and components (Refer to SRM

51-24-00):

Corrosion Inhibiting

Brush Consistency

09-013 As required

(k) Install rivets immediately after you position the components with sealant. If not,

tacking pins must be installed temporarily in every third hole.

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 68

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

(l) After riveting, remove unwanted sealant from the work area and apply to the rivets:

Anti-Corrosion

Primer

(polyurethane)

16-001 As required

External Top Coat

(polyurethane)

16-018 As required

(m) Where locking facilities exist, make sure that the electrical connector is correctly

locked with:

Lockwire, Stainless

Steel, Annealed,

0.8mm Dia.

19-010 As required

(n) For the protective treatment in the upper area between Frame 80/82 thru Frame

91A, use:

Corrosion

Preventive

Temporary

Protective

Compound

15-005 As required

Corrosion

Preventive

Temporary

Protective

Compound

15-007 As required

Corrosion

Preventive

Temporary

Protective

Compound

15-009 As required

(o) For wiring and routing (Refer to ESPM 20-33-10).

(p) Do not fully tighten the attachment parts and ties until all the wire harnesses are

checked by a continuity test.

NOTE: To prevent chaffing, make sure that the cable harness does not sag

between the attachment points.

(q) Do not shrink the sleeves and shrinkable parts until you do a continuity test of the

new wires.

(r) For sleeve shrinking (Refer to ESPM 20-42-12).

(s) For the installation of sleeves and shrinkable parts (Refer to Process and Material

Specification (PMS) 01-07-06 and Process and Material Specification (PMS)

01-07-89).

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 69

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

(t) For fastener installation and removal (metallic structure) (Refer to SRM 51-42-11).

(u) For fastener installation and removal (composite structure) (Refer to SRM

51-42-21).

(v) For the installation of placards (Refer to AMM 11-00-00, Page Block 001).

(w) Install Service Bulletin identification placards at each end of new or modified

electrical wires in a position where they can be easily seen and at approximately

every 1.50 m (59.0 in.).

(2) Subtask 364033-910-001-001 - 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

Lint-Free Cotton Cloth 19-003 As required

References

Aircraft Maintenance Manual (AMM) 06-31-53, Page Block 001

06-41-53, Page Block 001

11-00-00, Page Block 201

Task 20-21-15-912-801

Elec. Std. Practices Manual (ESPM) 20-33-00

20-43-10

20-43-42

20-48-00

Standards Manual (SM)

Structural Repair Manual (SRM) 51-23-12

51-24-00

51-43-00

51-47-00

(a) Use a non metallic spatula to remove the sealant and clean the areas with :

Solvent General

Purpose

11-026 As required

(b) For fasteners spacing and margin (Refer to SRM 51-47-00).

(c) To torque tighten the electrical component fasteners (Refer to AMM Task

20-21-15-912-801).

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 70

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

(d) Clean the areas where you will install the placards with :

Solvent General

Purpose

11-026 As required

and

Lint-Free Cotton

Cloth

19-003 As required

(e) Apply the sealant (Refer to SRM 51-24-00).

(f) For the frames (FR) identification, (Refer to AMM 06-31-53, Page Block 001).

(g) For the identification of the access panels, (Refer to AMM 06-41-53, Page Block

001).

(h) Tag all the parts you must remove and retain to make the subsequent installation

easier.

(i) Put all the retained hardware in identified plastic bags and attach the bags to the

related unit.

(j) 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 the

Standards Manual (SM). The SM will give you the correct part number to part

number relationship.

(k) For the installation of the placards, (Refer to AMM 11-00-00, Page Block 201).

(l) Apply a special protection on new parts (Refer to SRM 51-23-12).

(m) Obey the instructions for the general wiring installation, (Refer to ESPM 20-33-00).

(n) Obey the instructions of the pressure seals (Refer to ESPM 20-43-42).

(o) Obey the instructions of the splices installation (Refer to ESPM 20-43-10).

(p) Make sure that the electrical connectors are serviceable before you connect them

again.

(q) To install new wires, cut them to the necessary length, crimp the terminals and

connect them (Refer to ESPM 20-48-00).

(r) Put blanking plugs on the disconnected line ends.

(3) Subtask 364033-839-201-001 - 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.

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 71

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 004

(1) Subtask 364033-910-201-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

Material necessary to do the job

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Adhesive Sealant 08-004 As required

Corrosion Inhibiting Brush

Consistency

09-013 As required

Corrosion Inhibiting, Fillet

Consistency

09-016 As required

Low Adhesion Polysulfide

Sealant

09-019 As required

Chemical Conversion

Coating Yellow Aluminum

13-002 As required

Corrosion Preventive

Temporary Protective

Compound

15-005 As required

Corrosion Preventive

Temporary Protective

Compound

15-007 As required

Corrosion Preventive

Temporary Protective

Compound

15-009 As required

Anti-Corrosion Primer

(polyurethane)

16-001 As required

Anti-Corrosion Primer

(Epoxy-Improved Adhesion)

16-006 As required

External Top Coat

(polyurethane)

16-018 As required

Wash Primer 16-020 As required

Lockwire, Stainless Steel,

Annealed, 0.8mm Dia.

19-010 As required

References

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

11-00-00, Page Block 001

Elec. Std. Practices Manual (ESPM) 20-33-10

20-42-12

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 72

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

References

Process and Material Specification

(PMS)

Process and Material Specification (PMS)

01-02-36

Process and Material Specification (PMS)

01-07-06

Process and Material Specification (PMS)

01-07-89

Standards Manual (SM)

Structural Repair Manual (SRM) 51-24-00

51-42-11

51-42-21

51-75-12

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

to the Consumable Materials List (CML)).

(b) For the identification of Zones (Refer to AMM 06-20-00, Page Block 001).

(c) For the application of low adhesion sealants (Refer to Process and Material

Specification (PMS) 01-02-36).

(d) Renew the protective finish (Refer to SRM 51-75-12).

(e) Apply:

Low Adhesion

Polysulfide Sealant

09-019 As required

to the interfaces of the structure and the mew parts.

(f) Fill gaps between the structure with:

Corrosion Inhibiting,

Fillet Consistency

09-016 As required

Low Adhesion

Polysulfide Sealant

09-019 As required

Adhesive Sealant 08-004 As required

(g) Protect the spot facing area with:

Chemical

Conversion Coating

Yellow Aluminum

13-002 As required

Anti-Corrosion

Primer

(polyurethane)

16-001 As required

External Top Coat

(polyurethane)

16-018 As required

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 73

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

(h) For the drilling of rivet holes:

- Use a soft lead pencil and make marks to show the position of the rivet holes.

- Make sure that you have the correct edge clearance before you drill the

fastener holes.

- If not shown otherwise the tolerance for rivet holes is + 0.1 mm (+ 0.004 in.).

- Transfer-drill the existing holes with a pilot drill and a drill bush.

- Deburr the holes after you have drilled them.

- Cut the rivets to the correct length, as necessary.

- When you remove fasteners you must be careful that you do not damage the

holes in the structure.

- Drill new fastener holes with a pilot drill of 2.5 mm (0.098 in.) diameter.

Increase the hole diameter to the correct size for the fastener which you must

install.

(i) Apply:

Wash Primer 16-020 As required

Anti-Corrosion

Primer (EpoxyImproved Adhesion)

16-006 As required

to the new drilled holes.

(j) Before riveting apply to all contact surfaces and components (Refer to SRM

51-24-00):

Corrosion Inhibiting

Brush Consistency

09-013 As required

(k) Install rivets immediately after you position the components with sealant. If not,

tacking pins must be installed temporarily in every third hole.

(l) After riveting, remove unwanted sealant from the work area and apply to the rivets:

Anti-Corrosion

Primer

(polyurethane)

16-001 As required

External Top Coat

(polyurethane)

16-018 As required

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 74

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

(m) Where locking facilities exist, make sure that the electrical connector is correctly

locked with:

Lockwire, Stainless

Steel, Annealed,

0.8mm Dia.

19-010 As required

(n) For the protective treatment in the upper area between Frame 80/82 thru Frame

91A, use:

Corrosion

Preventive

Temporary

Protective

Compound

15-005 As required

Corrosion

Preventive

Temporary

Protective

Compound

15-007 As required

Corrosion

Preventive

Temporary

Protective

Compound

15-009 As required

(o) For wiring and routing (Refer to ESPM 20-33-10).

(p) Do not fully tighten the attachment parts and ties until all the wire harnesses are

checked by a continuity test.

NOTE: To prevent chaffing, make sure that the cable harness does not sag

between the attachment points.

(q) Do not shrink the sleeves and shrinkable parts until you do a continuity test of the

new wires.

(r) For sleeve shrinking (Refer to ESPM 20-42-12).

(s) For the installation of sleeves and shrinkable parts (Refer to Process and Material

Specification (PMS) 01-07-06 and Process and Material Specification (PMS)

01-07-89).

(t) For fastener installation and removal (metallic structure) (Refer to SRM 51-42-11).

(u) For fastener installation and removal (composite structure) (Refer to SRM

51-42-21).

(v) For the installation of placards (Refer to AMM 11-00-00, Page Block 001).

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 75

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

(w) Install Service Bulletin identification placards at each end of new or modified

electrical wires in a position where they can be easily seen and at approximately

every 1.50 m (59.0 in.).

(2) Subtask 364033-910-001-001 - 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

Lint-Free Cotton Cloth 19-003 As required

References

Aircraft Maintenance Manual (AMM) 06-31-53, Page Block 001

06-41-53, Page Block 001

11-00-00, Page Block 201

Task 20-21-15-912-801

Elec. Std. Practices Manual (ESPM) 20-33-00

20-43-10

20-43-42

20-48-00

Standards Manual (SM)

Structural Repair Manual (SRM) 51-23-12

51-24-00

51-43-00

51-47-00

(a) Use a non metallic spatula to remove the sealant and clean the areas with :

Solvent General

Purpose

11-026 As required

(b) For fasteners spacing and margin (Refer to SRM 51-47-00).

(c) To torque tighten the electrical component fasteners (Refer to AMM Task

20-21-15-912-801).

(d) Clean the areas where you will install the placards with :

Solvent General

Purpose

11-026 As required

and

Lint-Free Cotton

Cloth

19-003 As required

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(e) Apply the sealant (Refer to SRM 51-24-00).

(f) For the frames (FR) identification, (Refer to AMM 06-31-53, Page Block 001).

(g) For the identification of the access panels, (Refer to AMM 06-41-53, Page Block

001).

(h) Tag all the parts you must remove and retain to make the subsequent installation

easier.

(i) Put all the retained hardware in identified plastic bags and attach the bags to the

related unit.

(j) 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 the

Standards Manual (SM). The SM will give you the correct part number to part

number relationship.

(k) For the installation of the placards, (Refer to AMM 11-00-00, Page Block 201).

(l) Apply a special protection on new parts (Refer to SRM 51-23-12).

(m) Obey the instructions for the general wiring installation, (Refer to ESPM 20-33-00).

(n) Obey the instructions of the pressure seals (Refer to ESPM 20-43-42).

(o) Obey the instructions of the splices installation (Refer to ESPM 20-43-10).

(p) Make sure that the electrical connectors are serviceable before you connect them

again.

(q) To install new wires, cut them to the necessary length, crimp the terminals and

connect them (Refer to ESPM 20-48-00).

(r) Put blanking plugs on the disconnected line ends.

(3) Subtask 364033-839-201-001 - 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 005

(1) Subtask 364033-910-201-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 77

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SERVICE BULLETIN

Material necessary to do the job

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Adhesive Sealant 08-004 As required

Corrosion Inhibiting Brush

Consistency

09-013 As required

Corrosion Inhibiting, Fillet

Consistency

09-016 As required

Low Adhesion Polysulfide

Sealant

09-019 As required

Chemical Conversion

Coating Yellow Aluminum

13-002 As required

Corrosion Preventive

Temporary Protective

Compound

15-005 As required

Corrosion Preventive

Temporary Protective

Compound

15-007 As required

Corrosion Preventive

Temporary Protective

Compound

15-009 As required

Anti-Corrosion Primer

(polyurethane)

16-001 As required

Anti-Corrosion Primer

(Epoxy-Improved Adhesion)

16-006 As required

External Top Coat

(polyurethane)

16-018 As required

Wash Primer 16-020 As required

Lockwire, Stainless Steel,

Annealed, 0.8mm Dia.

19-010 As required

References

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

11-00-00, Page Block 001

Elec. Std. Practices Manual (ESPM) 20-33-10

20-42-12

Process and Material Specification

(PMS)

Process and Material Specification (PMS)

01-02-36

Process and Material Specification (PMS)

01-07-06

Process and Material Specification (PMS)

01-07-89

Standards Manual (SM)

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 78

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References

Structural Repair Manual (SRM) 51-24-00

51-42-11

51-42-21

51-75-12

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

to the Consumable Materials List (CML)).

(b) For the identification of Zones (Refer to AMM 06-20-00, Page Block 001).

(c) For the application of low adhesion sealants (Refer to Process and Material

Specification (PMS) 01-02-36).

(d) Renew the protective finish (Refer to SRM 51-75-12).

(e) Apply:

Low Adhesion

Polysulfide Sealant

09-019 As required

to the interfaces of the structure and the mew parts.

(f) Fill gaps between the structure with:

Corrosion Inhibiting,

Fillet Consistency

09-016 As required

Low Adhesion

Polysulfide Sealant

09-019 As required

Adhesive Sealant 08-004 As required

(g) Protect the spot facing area with:

Chemical

Conversion Coating

Yellow Aluminum

13-002 As required

Anti-Corrosion

Primer

(polyurethane)

16-001 As required

External Top Coat

(polyurethane)

16-018 As required

(h) For the drilling of rivet holes:

- Use a soft lead pencil and make marks to show the position of the rivet holes.

- Make sure that you have the correct edge clearance before you drill the

fastener holes.

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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- If not shown otherwise the tolerance for rivet holes is + 0.1 mm (+ 0.004 in.).

- Transfer-drill the existing holes with a pilot drill and a drill bush.

- Deburr the holes after you have drilled them.

- Cut the rivets to the correct length, as necessary.

- When you remove fasteners you must be careful that you do not damage the

holes in the structure.

- Drill new fastener holes with a pilot drill of 2.5 mm (0.098 in.) diameter.

Increase the hole diameter to the correct size for the fastener which you must

install.

(i) Apply:

Wash Primer 16-020 As required

Anti-Corrosion

Primer (EpoxyImproved Adhesion)

16-006 As required

to the new drilled holes.

(j) Before riveting apply to all contact surfaces and components (Refer to SRM

51-24-00):

Corrosion Inhibiting

Brush Consistency

09-013 As required

(k) Install rivets immediately after you position the components with sealant. If not,

tacking pins must be installed temporarily in every third hole.

(l) After riveting, remove unwanted sealant from the work area and apply to the rivets:

Anti-Corrosion

Primer

(polyurethane)

16-001 As required

External Top Coat

(polyurethane)

16-018 As required

(m) Where locking facilities exist, make sure that the electrical connector is correctly

locked with:

Lockwire, Stainless

Steel, Annealed,

0.8mm Dia.

19-010 As required

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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(n) For the protective treatment in the upper area between Frame 80/82 thru Frame

91A, use:

Corrosion

Preventive

Temporary

Protective

Compound

15-005 As required

Corrosion

Preventive

Temporary

Protective

Compound

15-007 As required

Corrosion

Preventive

Temporary

Protective

Compound

15-009 As required

(o) For wiring and routing (Refer to ESPM 20-33-10).

(p) Do not fully tighten the attachment parts and ties until all the wire harnesses are

checked by a continuity test.

NOTE: To prevent chaffing, make sure that the cable harness does not sag

between the attachment points.

(q) Do not shrink the sleeves and shrinkable parts until you do a continuity test of the

new wires.

(r) For sleeve shrinking (Refer to ESPM 20-42-12).

(s) For the installation of sleeves and shrinkable parts (Refer to Process and Material

Specification (PMS) 01-07-06 and Process and Material Specification (PMS)

01-07-89).

(t) For fastener installation and removal (metallic structure) (Refer to SRM 51-42-11).

(u) For fastener installation and removal (composite structure) (Refer to SRM

51-42-21).

(v) For the installation of placards (Refer to AMM 11-00-00, Page Block 001).

(w) Install Service Bulletin identification placards at each end of new or modified

electrical wires in a position where they can be easily seen and at approximately

every 1.50 m (59.0 in.).

(2) Subtask 364033-910-001-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 81

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SERVICE BULLETIN

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

Lint-Free Cotton Cloth 19-003 As required

References

Aircraft Maintenance Manual (AMM) 06-31-53, Page Block 001

06-41-53, Page Block 001

11-00-00, Page Block 201

Task 20-21-15-912-801

Elec. Std. Practices Manual (ESPM) 20-33-00

20-43-10

20-43-42

20-48-00

Standards Manual (SM)

Structural Repair Manual (SRM) 51-23-12

51-24-00

51-43-00

51-47-00

(a) Use a non metallic spatula to remove the sealant and clean the areas with :

Solvent General

Purpose

11-026 As required

(b) For fasteners spacing and margin (Refer to SRM 51-47-00).

(c) To torque tighten the electrical component fasteners (Refer to AMM Task

20-21-15-912-801).

(d) Clean the areas where you will install the placards with :

Solvent General

Purpose

11-026 As required

and

Lint-Free Cotton

Cloth

19-003 As required

(e) Apply the sealant (Refer to SRM 51-24-00).

(f) For the frames (FR) identification, (Refer to AMM 06-31-53, Page Block 001).

(g) For the identification of the access panels, (Refer to AMM 06-41-53, Page Block

001).

(h) Tag all the parts you must remove and retain to make the subsequent installation

easier.

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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(i) Put all the retained hardware in identified plastic bags and attach the bags to the

related unit.

(j) 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 the

Standards Manual (SM). The SM will give you the correct part number to part

number relationship.

(k) For the installation of the placards, (Refer to AMM 11-00-00, Page Block 201).

(l) Apply a special protection on new parts (Refer to SRM 51-23-12).

(m) Obey the instructions for the general wiring installation, (Refer to ESPM 20-33-00).

(n) Obey the instructions of the pressure seals (Refer to ESPM 20-43-42).

(o) Obey the instructions of the splices installation (Refer to ESPM 20-43-10).

(p) Make sure that the electrical connectors are serviceable before you connect them

again.

(q) To install new wires, cut them to the necessary length, crimp the terminals and

connect them (Refer to ESPM 20-48-00).

(r) Put blanking plugs on the disconnected line ends.

(3) Subtask 364033-839-201-001 - 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 364033-941-201-001 - Job Set-up

Work Zones and Access Panels

Zone Access/Work location

130 Access Door 831, Door 821

Work location from Frame 20 to Frame 39.2

Panel 132CC

Panel 132GC

Panel 132KC

Panel 132MC

Panel 132PC

Panel 132RC

Panel 132TC

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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150 Access Door 822

160 Access Door 313AL

Work location Panel 161BC

Panel 161EC

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 25-52-00, Page Block 201

25-54-00, Page Block 201

52-33-00, Page Block 001

(a) In the FWD cargo compartment remove the ceiling panels 132CC, 132GC, 132KC,

132MC, 132PC, 132RC and 132TC for access as necessary (Refer to AMM

25-52-00, Page Block 201).

(b) Open the Bulk cargo compartment door (Refer to AMM 52-33-00, Page Block 001).

(c) In the BULK cargo compartment remove the ceiling panels 161BC and 161EC for

access as necessary (Refer to AMM 25-54-00, Page Block 201).

(2) Subtask 364033-941-001-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-41-52, Page Block 001

06-41-53, Page Block 001

Task 12-34-24-860-802

Task 32-12-00-010-801

Task 36-11-34-000-802

Task 36-22-17-000-801

Task 36-22-17-000-802

Task 52-10-00-010-801

52-30-00, Page Block 201

52-52-00, Page Block 001

(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.

(c) Open the passenger/crew door(s) (Refer to AMM Task 52-10-00-010-801).

(d) Open the FWD cargo-compartment door 821 and AFT cargo-compartment door 822

(Refer to AMM 06-41-52, Page Block 001 and AMM 52-30-00, Page Block 201).

(e) Open the door 132AZ (Refer to AMM 06-41-53, Page Block 001 and AMM

52-52-00, Page Block 001).

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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(f) Open the Main Landing Gear (MLG) doors (Refer to AMM Task 32-12-00-010-801).

(g) Do the Job Set-up procedure as specified in the removal of the sensing elements

(Refer to AMM Task 36-22-17-000-801 and AMM Task 36-22-17-000-802).

(h) Do the Job Set-up procedure as specified in the removal of the Bleed Monitoring

Computer (BMC) (FIN 1HA1, 1HA2, 1HA3 and 1HA4) (Refer to AMM Task

36-11-34-000-802).

(3) Subtask 364033-010-001-001 - Remove/Open for Access

Manpower Resources

Skills NON SPECIFIC

References

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

Task 25-21-41-000-801

Task 25-28-41-000-801

Task 25-52-00-000-801

Task 25-53-00-000-801

Task 25-53-00-000-801

Task 25-75-41-000-801

Task 53-00-00-000-801

Task 53-00-00-000-802

Task 53-35-11-000-801

Task 53-35-13-000-801

Task 53-35-13-000-802

(a) Between Frame 37.4 and Frame 39.1 in the FWD cargo-compartment, remove the

floor panel 132DG (Refer to AMM 06-41-53, Page Block 001 and AMM Task

53-00-00-000-802).

(b) On the RH side, between Frame 38 and Frame 39.1 in the FWD cargocompartment, remove (if necessary) the sidewall panels 132AX and 132ZW (Refer

to AMM 06-41-53, Page Block 001 and AMM Task 25-52-00-000-801).

(c) On the RH side, between Frame 37.1 and Frame 39.1 in the FWD cargocompartment, remove (if necessary) the ceiling panels 132TC and 132VC (Refer to

AMM 06-41-53, Page Block 001 and AMM Task 25-52-00-000-801).

(d) At Frame 39.2 in the FWD cargo-compartment, remove (if necessary) the partition

panels 132DX and 132CX (Refer to AMM 06-41-53, Page Block 001 and AMM

Task 25-52-00-000-801).

(e) At Frame 20 in the FWD cargo-compartment, remove the partition panels

131AW and 132CW (Refer to AMM 06-41-53, Page Block 001 and AMM Task

25-52-00-000-801).

(f) On the RH side only, between Frame 47 and Frame 53 in the PAX compartment,

remove (if necessary) the Seats (Refer to AMM Task 25-21-41-000-801).

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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(g) On the RH side only, between Frame 47 and Frame 53 in the PAX compartment,

remove (if necessary) the Textile Floor (TF) Covering for access to the spare

conduits (Refer to AMM Task 25-28-41-000-801).

(h) On the RH side, between Frame 47 and Frame 53 in the PAX compartment,

remove (if necessary) the floor panel 252LG for access to the spare conduits (Refer

to AMM Task 53-00-00-000-801).

(i) On the LH side, between Frame 53.2 and Frame 57.1 in the AFT cargo

compartment, remove (if necessary) the sidewall panels 151EW, 151GW

and 151JW (Refer to AMM 06-41-53, Page Block 001 and AMM Task

25-53-00-000-801).

(j) On the RH side, between Frame 53.2 and Frame 58 in the AFT cargocompartment, remove (if necessary) the ceiling panels 152BC, 152DC, 152FC

and 152HC (Refer to AMM 06-41-53, Page Block 001 and AMM Task

25-53-00-000-801).

(k) At Frame 53.2 in the AFT cargo-compartment, remove the partition panel 152CW

(Refer to AMM 06-41-53, Page Block 001 and AMM Task 25-53-00-000-801).

(l) On the LH side of the belly fairing, remove (if necessary) the panels 191HB,

191FB, 191KB, 193AB, 195CB, 195DB, 197AT, 197BB and 197EB (Refer to

AMM Task 53-35-11-000-801 and AMM Task 53-35-13-000-801 and AMM Task

53-35-13-000-802).

(m) On the RH side of the belly fairing, remove the panels 192BZ, 192CZ, 192HB and

192GB (Refer to AMM Task 53-35-11-000-801 and AMM Task 53-35-13-000-802).

(n) If existing, remove the Lower Deck Mobile Crew Rest (LD-MCR) (Refer to AMM

Task 25-75-41-000-801).

(4) Subtask 364033-862-001-001 - De-energize Electrical Network (Safety Precautions).

Manpower Resources

Skills NON SPECIFIC

(a) In the cockpit, on the panel 235VU, make sure that these pushbutton switches are

released :

- BAT 1, BAT 2, APU BAT,

- GEN 1, (2, 3, 4), APU GEN,

- EXT A (B).

(b) Open, safety and tags the following circuit breakers:

PANEL DESIGNATION FIN LOCATION SEE

NOTES

742VU 701PP 10PB1 72 S

742VU 702PP 10PB2 71 S

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(c) Make sure that there is (are) warning notice(s) in the cockpit to tell persons not to

operate the pushbutton switches on the overhead panel :

- 211VU (EMER ELEC PWR),

- 235VU (ELEC).

(d) Make sure that there is (are) warning notice(s) in the cockpit to tell persons not to

start the APU.

(e) Make sure that the external connector(s) is (are) not connected to the aircraft

receptacle(s) EXT PWR A (B).

(f) Make sure that there is a warning notice at the access door 121EL to tell persons

not to connect the external power connector (s).

**CONF 002

(1) Subtask 364033-941-201-001 - Job Set-up

Work Zones and Access Panels

Zone Access/Work location

130 Access Door 831, Door 821

Work location from Frame 20 to Frame 39.2

Panel 132CC

Panel 132GC

Panel 132KC

Panel 132MC

Panel 132PC

Panel 132RC

Panel 132TC

150 Access Door 822

160 Access Door 313AL

Work location Panel 161BC

Panel 161EC

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 25-52-00, Page Block 201

25-54-00, Page Block 201

52-33-00, Page Block 001

(a) In the FWD cargo compartment remove the ceiling panels 132CC, 132GC, 132KC,

132MC, 132PC, 132RC and 132TC for access as necessary (Refer to AMM

25-52-00, Page Block 201).

(b) Open the Bulk cargo compartment door (Refer to AMM 52-33-00, Page Block 001).

(c) In the BULK cargo compartment remove the ceiling panels 161BC and 161EC for

access as necessary (Refer to AMM 25-54-00, Page Block 201).

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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(2) Subtask 364033-941-001-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-41-52, Page Block 001

06-41-53, Page Block 001

Task 12-34-24-860-802

Task 32-12-00-010-801

Task 36-11-34-000-802

Task 36-22-17-000-801

Task 36-22-17-000-802

Task 52-10-00-010-801

52-30-00, Page Block 201

52-52-00, Page Block 001

(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.

(c) Open the passenger/crew door(s) (Refer to AMM Task 52-10-00-010-801).

(d) Open the FWD cargo-compartment door 821 and AFT cargo-compartment door 822

(Refer to AMM 06-41-52, Page Block 001 and AMM 52-30-00, Page Block 201).

(e) Open the door 132AZ (Refer to AMM 06-41-53, Page Block 001 and AMM

52-52-00, Page Block 001).

(f) Open the Main Landing Gear (MLG) doors (Refer to AMM Task 32-12-00-010-801).

(g) Do the Job Set-up procedure as specified in the removal of the sensing elements

(Refer to AMM Task 36-22-17-000-801 and AMM Task 36-22-17-000-802).

(h) Do the Job Set-up procedure as specified in the removal of the Bleed Monitoring

Computer (BMC) (FIN 1HA1, 1HA2, 1HA3 and 1HA4) (Refer to AMM Task

36-11-34-000-802).

(3) Subtask 364033-010-001-001 - Remove/Open for Access

Manpower Resources

Skills NON SPECIFIC

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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References

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

Task 25-21-41-000-801

Task 25-28-41-000-801

Task 25-52-00-000-801

Task 25-53-00-000-801

Task 25-53-00-000-801

Task 25-75-41-000-801

Task 53-00-00-000-801

Task 53-00-00-000-802

Task 53-35-11-000-801

Task 53-35-13-000-801

Task 53-35-13-000-802

(a) Between Frame 37.4 and Frame 39.1 in the FWD cargo-compartment, remove the

floor panel 132DG (Refer to AMM 06-41-53, Page Block 001 and AMM Task

53-00-00-000-802).

(b) On the RH side, between Frame 38 and Frame 39.1 in the FWD cargocompartment, remove (if necessary) the sidewall panels 132AX and 132ZW (Refer

to AMM 06-41-53, Page Block 001 and AMM Task 25-52-00-000-801).

(c) On the RH side, between Frame 37.1 and Frame 39.1 in the FWD cargocompartment, remove (if necessary) the ceiling panels 132TC and 132VC (Refer to

AMM 06-41-53, Page Block 001 and AMM Task 25-52-00-000-801).

(d) At Frame 39.2 in the FWD cargo-compartment, remove (if necessary) the partition

panels 132DX and 132CX (Refer to AMM 06-41-53, Page Block 001 and AMM

Task 25-52-00-000-801).

(e) At Frame 20 in the FWD cargo-compartment, remove the partition panels

131AW and 132CW (Refer to AMM 06-41-53, Page Block 001 and AMM Task

25-52-00-000-801).

(f) On the RH side only, between Frame 47 and Frame 53 in the PAX compartment,

remove (if necessary) the Seats (Refer to AMM Task 25-21-41-000-801).

(g) On the RH side only, between Frame 47 and Frame 53 in the PAX compartment,

remove (if necessary) the Textile Floor (TF) Covering for access to the spare

conduits (Refer to AMM Task 25-28-41-000-801).

(h) On the RH side, between Frame 47 and Frame 53 in the PAX compartment,

remove (if necessary) the floor panel 252LG for access to the spare conduits (Refer

to AMM Task 53-00-00-000-801).

(i) On the LH side, between Frame 53.2 and Frame 57.1 in the AFT cargo

compartment, remove (if necessary) the sidewall panels 151EW, 151GW

and 151JW (Refer to AMM 06-41-53, Page Block 001 and AMM Task

25-53-00-000-801).

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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(j) On the RH side, between Frame 53.2 and Frame 58 in the AFT cargocompartment, remove (if necessary) the ceiling panels 152BC, 152DC, 152FC

and 152HC (Refer to AMM 06-41-53, Page Block 001 and AMM Task

25-53-00-000-801).

(k) At Frame 53.2 in the AFT cargo-compartment, remove the partition panel 152CW

(Refer to AMM 06-41-53, Page Block 001 and AMM Task 25-53-00-000-801).

(l) On the LH side of the belly fairing, remove (if necessary) the panels 191HB,

191FB, 191KB, 193AB, 195CB, 195DB, 197AT, 197BB and 197EB (Refer to

AMM Task 53-35-11-000-801 and AMM Task 53-35-13-000-801 and AMM Task

53-35-13-000-802).

(m) On the RH side of the belly fairing, remove the panels 192BZ, 192CZ, 192HB and

192GB (Refer to AMM Task 53-35-11-000-801 and AMM Task 53-35-13-000-802).

(n) If existing, remove the Lower Deck Mobile Crew Rest (LD-MCR) (Refer to AMM

Task 25-75-41-000-801).

(4) Subtask 364033-862-001-001 - De-energize Electrical Network (Safety Precautions).

Manpower Resources

Skills NON SPECIFIC

(a) In the cockpit, on the panel 235VU, make sure that these pushbutton switches are

released :

- BAT 1, BAT 2, APU BAT,

- GEN 1, (2, 3, 4), APU GEN,

- EXT A (B).

(b) Open, safety and tags the following circuit breakers:

PANEL DESIGNATION FIN LOCATION SEE

NOTES

742VU 701PP 10PB1 72 S

742VU 702PP 10PB2 71 S

(c) Make sure that there is (are) warning notice(s) in the cockpit to tell persons not to

operate the pushbutton switches on the overhead panel :

- 211VU (EMER ELEC PWR),

- 235VU (ELEC).

(d) Make sure that there is (are) warning notice(s) in the cockpit to tell persons not to

start the APU.

(e) Make sure that the external connector(s) is (are) not connected to the aircraft

receptacle(s) EXT PWR A (B).

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 90

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SERVICE BULLETIN

(f) Make sure that there is a warning notice at the access door 121EL to tell persons

not to connect the external power connector (s).

**CONF 003

(1) Subtask 364033-941-201-001 - Job Set-up

Work Zones and Access Panels

Zone Access/Work location

130 Access Door 831, Door 821

Work location from Frame 20 to Frame 39.2

Panel 132CC

Panel 132GC

Panel 132KC

Panel 132MC

Panel 132PC

Panel 132RC

Panel 132TC

150 Access Door 822

160 Access Door 313AL

Work location Panel 161BC

Panel 161EC

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 25-52-00, Page Block 201

25-54-00, Page Block 201

52-33-00, Page Block 001

(a) In the FWD cargo compartment remove the ceiling panels 132CC, 132GC, 132KC,

132MC, 132PC, 132RC and 132TC for access as necessary (Refer to AMM

25-52-00, Page Block 201).

(b) Open the Bulk cargo compartment door (Refer to AMM 52-33-00, Page Block 001).

(c) In the BULK cargo compartment remove the ceiling panels 161BC and 161EC for

access as necessary (Refer to AMM 25-54-00, Page Block 201).

(2) Subtask 364033-941-001-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 91

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@A340

SERVICE BULLETIN

References

Aircraft Maintenance Manual (AMM) 06-41-52, Page Block 001

06-41-53, Page Block 001

Task 12-34-24-860-802

Task 32-12-00-010-801

Task 36-11-34-000-802

Task 36-22-17-000-801

Task 36-22-17-000-802

Task 52-10-00-010-801

52-30-00, Page Block 201

52-52-00, Page Block 001

(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.

(c) Open the passenger/crew door(s) (Refer to AMM Task 52-10-00-010-801).

(d) Open the FWD cargo-compartment door 821 and AFT cargo-compartment door 822

(Refer to AMM 06-41-52, Page Block 001 and AMM 52-30-00, Page Block 201).

(e) Open the door 132AZ (Refer to AMM 06-41-53, Page Block 001 and AMM

52-52-00, Page Block 001).

(f) Open the Main Landing Gear (MLG) doors (Refer to AMM Task 32-12-00-010-801).

(g) Do the Job Set-up procedure as specified in the removal of the sensing elements

(Refer to AMM Task 36-22-17-000-801 and AMM Task 36-22-17-000-802).

(h) Do the Job Set-up procedure as specified in the removal of the Bleed Monitoring

Computer (BMC) (FIN 1HA1, 1HA2, 1HA3 and 1HA4) (Refer to AMM Task

36-11-34-000-802).

(3) Subtask 364033-010-001-001 - Remove/Open for Access

Manpower Resources

Skills NON SPECIFIC

References

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

Task 25-21-41-000-801

Task 25-28-41-000-801

Task 25-52-00-000-801

Task 25-53-00-000-801

Task 25-53-00-000-801

Task 25-75-41-000-801

Task 53-00-00-000-801

Task 53-00-00-000-802

Task 53-35-11-000-801

Task 53-35-13-000-801

Task 53-35-13-000-802

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 92

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(a) Between Frame 37.4 and Frame 39.1 in the FWD cargo-compartment, remove the

floor panel 132DG (Refer to AMM 06-41-53, Page Block 001 and AMM Task

53-00-00-000-802).

(b) On the RH side, between Frame 38 and Frame 39.1 in the FWD cargocompartment, remove (if necessary) the sidewall panels 132AX and 132ZW (Refer

to AMM 06-41-53, Page Block 001 and AMM Task 25-52-00-000-801).

(c) On the RH side, between Frame 37.1 and Frame 39.1 in the FWD cargocompartment, remove (if necessary) the ceiling panels 132TC and 132VC (Refer to

AMM 06-41-53, Page Block 001 and AMM Task 25-52-00-000-801).

(d) At Frame 39.2 in the FWD cargo-compartment, remove (if necessary) the partition

panels 132DX and 132CX (Refer to AMM 06-41-53, Page Block 001 and AMM

Task 25-52-00-000-801).

(e) At Frame 20 in the FWD cargo-compartment, remove the partition panels

131AW and 132CW (Refer to AMM 06-41-53, Page Block 001 and AMM Task

25-52-00-000-801).

(f) On the RH side only, between Frame 47 and Frame 53 in the PAX compartment,

remove (if necessary) the Seats (Refer to AMM Task 25-21-41-000-801).

(g) On the RH side only, between Frame 47 and Frame 53 in the PAX compartment,

remove (if necessary) the Textile Floor (TF) Covering for access to the spare

conduits (Refer to AMM Task 25-28-41-000-801).

(h) On the RH side, between Frame 47 and Frame 53 in the PAX compartment,

remove (if necessary) the floor panel 252LG for access to the spare conduits (Refer

to AMM Task 53-00-00-000-801).

(i) On the LH side, between Frame 53.2 and Frame 57.1 in the AFT cargo

compartment, remove (if necessary) the sidewall panels 151EW, 151GW

and 151JW (Refer to AMM 06-41-53, Page Block 001 and AMM Task

25-53-00-000-801).

(j) On the RH side, between Frame 53.2 and Frame 58 in the AFT cargocompartment, remove (if necessary) the ceiling panels 152BC, 152DC, 152FC

and 152HC (Refer to AMM 06-41-53, Page Block 001 and AMM Task

25-53-00-000-801).

(k) At Frame 53.2 in the AFT cargo-compartment, remove the partition panel 152CW

(Refer to AMM 06-41-53, Page Block 001 and AMM Task 25-53-00-000-801).

(l) On the LH side of the belly fairing, remove (if necessary) the panels 191HB,

191FB, 191KB, 193AB, 195CB, 195DB, 197AT, 197BB and 197EB (Refer to

AMM Task 53-35-11-000-801 and AMM Task 53-35-13-000-801 and AMM Task

53-35-13-000-802).

(m) On the RH side of the belly fairing, remove the panels 192BZ, 192CZ, 192HB and

192GB (Refer to AMM Task 53-35-11-000-801 and AMM Task 53-35-13-000-802).

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 93

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@A340

SERVICE BULLETIN

(n) If existing, remove the Lower Deck Mobile Crew Rest (LD-MCR) (Refer to AMM

Task 25-75-41-000-801).

(4) Subtask 364033-862-001-001 - De-energize Electrical Network (Safety Precautions).

Manpower Resources

Skills NON SPECIFIC

(a) In the cockpit, on the panel 235VU, make sure that these pushbutton switches are

released :

- BAT 1, BAT 2, APU BAT,

- GEN 1, (2, 3, 4), APU GEN,

- EXT A (B).

(b) Open, safety and tags the following circuit breakers:

PANEL DESIGNATION FIN LOCATION SEE

NOTES

742VU 701PP 10PB1 72 S

742VU 702PP 10PB2 71 S

(c) Make sure that there is (are) warning notice(s) in the cockpit to tell persons not to

operate the pushbutton switches on the overhead panel :

- 211VU (EMER ELEC PWR),

- 235VU (ELEC).

(d) Make sure that there is (are) warning notice(s) in the cockpit to tell persons not to

start the APU.

(e) Make sure that the external connector(s) is (are) not connected to the aircraft

receptacle(s) EXT PWR A (B).

(f) Make sure that there is a warning notice at the access door 121EL to tell persons

not to connect the external power connector (s).

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 94

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SERVICE BULLETIN

**CONF 004

(1) Subtask 364033-941-201-001 - Job Set-up

Work Zones and Access Panels

Zone Access/Work location

130 Access Door 831, Door 821

Work location from Frame 20 to Frame 39.2

Panel 132CC

Panel 132GC

Panel 132KC

Panel 132MC

Panel 132PC

Panel 132RC

Panel 132TC

150 Access Door 822

160 Access Door 313AL

Work location Panel 161BC

Panel 161EC

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 25-52-00, Page Block 201

25-54-00, Page Block 201

52-33-00, Page Block 001

(a) In the FWD cargo compartment remove the ceiling panels 132CC, 132GC, 132KC,

132MC, 132PC, 132RC and 132TC for access as necessary (Refer to AMM

25-52-00, Page Block 201).

(b) Open the Bulk cargo compartment door (Refer to AMM 52-33-00, Page Block 001).

(c) In the BULK cargo compartment remove the ceiling panels 161BC and 161EC for

access as necessary (Refer to AMM 25-54-00, Page Block 201).

(2) Subtask 364033-941-001-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 95

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@A340

SERVICE BULLETIN

References

Aircraft Maintenance Manual (AMM) 06-41-52, Page Block 001

06-41-53, Page Block 001

Task 12-34-24-860-802

Task 32-12-00-010-801

Task 36-11-34-000-802

Task 36-22-17-000-801

Task 36-22-17-000-802

Task 52-10-00-010-801

52-30-00, Page Block 201

52-52-00, Page Block 001

(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.

(c) Open the passenger/crew door(s) (Refer to AMM Task 52-10-00-010-801).

(d) Open the FWD cargo-compartment door 821 and AFT cargo-compartment door 822

(Refer to AMM 06-41-52, Page Block 001 and AMM 52-30-00, Page Block 201).

(e) Open the door 132AZ (Refer to AMM 06-41-53, Page Block 001 and AMM

52-52-00, Page Block 001).

(f) Open the Main Landing Gear (MLG) doors (Refer to AMM Task 32-12-00-010-801).

(g) Do the Job Set-up procedure as specified in the removal of the sensing elements

(Refer to AMM Task 36-22-17-000-801 and AMM Task 36-22-17-000-802).

(h) Do the Job Set-up procedure as specified in the removal of the Bleed Monitoring

Computer (BMC) (FIN 1HA1, 1HA2, 1HA3 and 1HA4) (Refer to AMM Task

36-11-34-000-802).

(3) Subtask 364033-010-001-001 - Remove/Open for Access

Manpower Resources

Skills NON SPECIFIC

References

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

Task 25-21-41-000-801

Task 25-28-41-000-801

Task 25-52-00-000-801

Task 25-53-00-000-801

Task 25-53-00-000-801

Task 25-75-41-000-801

Task 53-00-00-000-801

Task 53-00-00-000-802

Task 53-35-11-000-801

Task 53-35-13-000-801

Task 53-35-13-000-802

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 96

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(a) Between Frame 37.4 and Frame 39.1 in the FWD cargo-compartment, remove the

floor panel 132DG (Refer to AMM 06-41-53, Page Block 001 and AMM Task

53-00-00-000-802).

(b) On the RH side, between Frame 38 and Frame 39.1 in the FWD cargocompartment, remove (if necessary) the sidewall panels 132AX and 132ZW (Refer

to AMM 06-41-53, Page Block 001 and AMM Task 25-52-00-000-801).

(c) On the RH side, between Frame 37.1 and Frame 39.1 in the FWD cargocompartment, remove (if necessary) the ceiling panels 132TC and 132VC (Refer to

AMM 06-41-53, Page Block 001 and AMM Task 25-52-00-000-801).

(d) At Frame 39.2 in the FWD cargo-compartment, remove (if necessary) the partition

panels 132DX and 132CX (Refer to AMM 06-41-53, Page Block 001 and AMM

Task 25-52-00-000-801).

(e) At Frame 20 in the FWD cargo-compartment, remove the partition panels

131AW and 132CW (Refer to AMM 06-41-53, Page Block 001 and AMM Task

25-52-00-000-801).

(f) On the RH side only, between Frame 47 and Frame 53 in the PAX compartment,

remove (if necessary) the Seats (Refer to AMM Task 25-21-41-000-801).

(g) On the RH side only, between Frame 47 and Frame 53 in the PAX compartment,

remove (if necessary) the Textile Floor (TF) Covering for access to the spare

conduits (Refer to AMM Task 25-28-41-000-801).

(h) On the RH side, between Frame 47 and Frame 53 in the PAX compartment,

remove (if necessary) the floor panel 252LG for access to the spare conduits (Refer

to AMM Task 53-00-00-000-801).

(i) On the LH side, between Frame 53.2 and Frame 57.1 in the AFT cargo

compartment, remove (if necessary) the sidewall panels 151EW, 151GW

and 151JW (Refer to AMM 06-41-53, Page Block 001 and AMM Task

25-53-00-000-801).

(j) On the RH side, between Frame 53.2 and Frame 58 in the AFT cargocompartment, remove (if necessary) the ceiling panels 152BC, 152DC, 152FC

and 152HC (Refer to AMM 06-41-53, Page Block 001 and AMM Task

25-53-00-000-801).

(k) At Frame 53.2 in the AFT cargo-compartment, remove the partition panel 152CW

(Refer to AMM 06-41-53, Page Block 001 and AMM Task 25-53-00-000-801).

(l) On the LH side of the belly fairing, remove (if necessary) the panels 191HB,

191FB, 191KB, 193AB, 195CB, 195DB, 197AT, 197BB and 197EB (Refer to

AMM Task 53-35-11-000-801 and AMM Task 53-35-13-000-801 and AMM Task

53-35-13-000-802).

(m) On the RH side of the belly fairing, remove the panels 192BZ, 192CZ, 192HB and

192GB (Refer to AMM Task 53-35-11-000-801 and AMM Task 53-35-13-000-802).

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 97

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@A340

SERVICE BULLETIN

(n) If existing, remove the Lower Deck Mobile Crew Rest (LD-MCR) (Refer to AMM

Task 25-75-41-000-801).

(4) Subtask 364033-862-001-001 - De-energize Electrical Network (Safety Precautions).

Manpower Resources

Skills NON SPECIFIC

(a) In the cockpit, on the panel 235VU, make sure that these pushbutton switches are

released :

- BAT 1, BAT 2, APU BAT,

- GEN 1, (2, 3, 4), APU GEN,

- EXT A (B).

(b) Open, safety and tags the following circuit breakers:

PANEL DESIGNATION FIN LOCATION SEE

NOTES

742VU 701PP 10PB1 72 S

742VU 702PP 10PB2 71 S

(c) Make sure that there is (are) warning notice(s) in the cockpit to tell persons not to

operate the pushbutton switches on the overhead panel :

- 211VU (EMER ELEC PWR),

- 235VU (ELEC).

(d) Make sure that there is (are) warning notice(s) in the cockpit to tell persons not to

start the APU.

(e) Make sure that the external connector(s) is (are) not connected to the aircraft

receptacle(s) EXT PWR A (B).

(f) Make sure that there is a warning notice at the access door 121EL to tell persons

not to connect the external power connector (s).

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 98

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SERVICE BULLETIN

**CONF 005

(1) Subtask 364033-941-201-001 - Job Set-up

Work Zones and Access Panels

Zone Access/Work location

130 Access Door 831, Door 821

Work location from Frame 20 to Frame 39.2

Panel 132CC

Panel 132GC

Panel 132KC

Panel 132MC

Panel 132PC

Panel 132RC

Panel 132TC

150 Access Door 822

160 Access Door 313AL

Work location Panel 161BC

Panel 161EC

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 25-52-00, Page Block 201

25-54-00, Page Block 201

52-33-00, Page Block 001

(a) In the FWD cargo compartment remove the ceiling panels 132CC, 132GC, 132KC,

132MC, 132PC, 132RC and 132TC for access as necessary (Refer to AMM

25-52-00, Page Block 201).

(b) Open the Bulk cargo compartment door (Refer to AMM 52-33-00, Page Block 001).

(c) In the BULK cargo compartment remove the ceiling panels 161BC and 161EC for

access as necessary (Refer to AMM 25-54-00, Page Block 201).

(2) Subtask 364033-941-001-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 99

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@A340

SERVICE BULLETIN

References

Aircraft Maintenance Manual (AMM) 06-41-52, Page Block 001

06-41-53, Page Block 001

Task 12-34-24-860-802

Task 32-12-00-010-801

Task 36-11-34-000-802

Task 36-22-17-000-801

Task 36-22-17-000-802

Task 52-10-00-010-801

52-30-00, Page Block 201

52-52-00, Page Block 001

(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.

(c) Open the passenger/crew door(s) (Refer to AMM Task 52-10-00-010-801).

(d) Open the FWD cargo-compartment door 821 and AFT cargo-compartment door 822

(Refer to AMM 06-41-52, Page Block 001 and AMM 52-30-00, Page Block 201).

(e) Open the door 132AZ (Refer to AMM 06-41-53, Page Block 001 and AMM

52-52-00, Page Block 001).

(f) Open the Main Landing Gear (MLG) doors (Refer to AMM Task 32-12-00-010-801).

(g) Do the Job Set-up procedure as specified in the removal of the sensing elements

(Refer to AMM Task 36-22-17-000-801 and AMM Task 36-22-17-000-802).

(h) Do the Job Set-up procedure as specified in the removal of the Bleed Monitoring

Computer (BMC) (FIN 1HA1, 1HA2, 1HA3 and 1HA4) (Refer to AMM Task

36-11-34-000-802).

(3) Subtask 364033-010-001-001 - Remove/Open for Access

Manpower Resources

Skills NON SPECIFIC

References

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

Task 25-21-41-000-801

Task 25-28-41-000-801

Task 25-52-00-000-801

Task 25-53-00-000-801

Task 25-53-00-000-801

Task 25-75-41-000-801

Task 53-00-00-000-801

Task 53-00-00-000-802

Task 53-35-11-000-801

Task 53-35-13-000-801

Task 53-35-13-000-802

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 100

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(a) Between Frame 37.4 and Frame 39.1 in the FWD cargo-compartment, remove the

floor panel 132DG (Refer to AMM 06-41-53, Page Block 001 and AMM Task

53-00-00-000-802).

(b) On the RH side, between Frame 38 and Frame 39.1 in the FWD cargocompartment, remove (if necessary) the sidewall panels 132AX and 132ZW (Refer

to AMM 06-41-53, Page Block 001 and AMM Task 25-52-00-000-801).

(c) On the RH side, between Frame 37.1 and Frame 39.1 in the FWD cargocompartment, remove (if necessary) the ceiling panels 132TC and 132VC (Refer to

AMM 06-41-53, Page Block 001 and AMM Task 25-52-00-000-801).

(d) At Frame 39.2 in the FWD cargo-compartment, remove (if necessary) the partition

panels 132DX and 132CX (Refer to AMM 06-41-53, Page Block 001 and AMM

Task 25-52-00-000-801).

(e) At Frame 20 in the FWD cargo-compartment, remove the partition panels

131AW and 132CW (Refer to AMM 06-41-53, Page Block 001 and AMM Task

25-52-00-000-801).

(f) On the RH side only, between Frame 47 and Frame 53 in the PAX compartment,

remove (if necessary) the Seats (Refer to AMM Task 25-21-41-000-801).

(g) On the RH side only, between Frame 47 and Frame 53 in the PAX compartment,

remove (if necessary) the Textile Floor (TF) Covering for access to the spare

conduits (Refer to AMM Task 25-28-41-000-801).

(h) On the RH side, between Frame 47 and Frame 53 in the PAX compartment,

remove (if necessary) the floor panel 252LG for access to the spare conduits (Refer

to AMM Task 53-00-00-000-801).

(i) On the LH side, between Frame 53.2 and Frame 57.1 in the AFT cargo

compartment, remove (if necessary) the sidewall panels 151EW, 151GW

and 151JW (Refer to AMM 06-41-53, Page Block 001 and AMM Task

25-53-00-000-801).

(j) On the RH side, between Frame 53.2 and Frame 58 in the AFT cargocompartment, remove (if necessary) the ceiling panels 152BC, 152DC, 152FC

and 152HC (Refer to AMM 06-41-53, Page Block 001 and AMM Task

25-53-00-000-801).

(k) At Frame 53.2 in the AFT cargo-compartment, remove the partition panel 152CW

(Refer to AMM 06-41-53, Page Block 001 and AMM Task 25-53-00-000-801).

(l) On the LH side of the belly fairing, remove (if necessary) the panels 191HB,

191FB, 191KB, 193AB, 195CB, 195DB, 197AT, 197BB and 197EB (Refer to

AMM Task 53-35-11-000-801 and AMM Task 53-35-13-000-801 and AMM Task

53-35-13-000-802).

(m) On the RH side of the belly fairing, remove the panels 192BZ, 192CZ, 192HB and

192GB (Refer to AMM Task 53-35-11-000-801 and AMM Task 53-35-13-000-802).

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 101

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@A340

SERVICE BULLETIN

(n) If existing, remove the Lower Deck Mobile Crew Rest (LD-MCR) (Refer to AMM

Task 25-75-41-000-801).

(4) Subtask 364033-862-001-001 - De-energize Electrical Network (Safety Precautions).

Manpower Resources

Skills NON SPECIFIC

(a) In the cockpit, on the panel 235VU, make sure that these pushbutton switches are

released :

- BAT 1, BAT 2, APU BAT,

- GEN 1, (2, 3, 4), APU GEN,

- EXT A (B).

(b) Open, safety and tags the following circuit breakers:

PANEL DESIGNATION FIN LOCATION SEE

NOTES

742VU 701PP 10PB1 72 S

742VU 702PP 10PB2 71 S

(c) Make sure that there is (are) warning notice(s) in the cockpit to tell persons not to

operate the pushbutton switches on the overhead panel :

- 211VU (EMER ELEC PWR),

- 235VU (ELEC).

(d) Make sure that there is (are) warning notice(s) in the cockpit to tell persons not to

start the APU.

(e) Make sure that the external connector(s) is (are) not connected to the aircraft

receptacle(s) EXT PWR A (B).

(f) Make sure that there is a warning notice at the access door 121EL to tell persons

not to connect the external power connector (s).

**CONF ALL

C. PROCEDURE

**CONF 001

(1) Subtask 364033-831-016-001 - Modify the Wiring between the Avionics

Compartment and the Cargo Compartment.

Work Zones and Access Panels

Zone Access/Work location

190

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Manpower Resources

Manhours 2.00

Minimum number of person 2

Subtask elapsed time 2.00

Skills ELECTRICAL

Material necessary to do the job

Kit 364033A02R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

169 NSA935401-03 300 TIE

F9000095227895 BUNDLE

NSA935401-08 300 TIE

NSA935401-13 300 TIE

References

Fig. A-FBMAA

Installation of the New Harness 2SG

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

Sheet 09

Sheet 10

Sheet 11

Sheet 12

Sheet 13

Sheet 14

Sheet 15

Sheet 16

Sheet 17

Sheet 18

Sheet 19

Sheet 20

Sheet 21

Sheet 22

Fig. A-FCBAA

Modification of the Wiring between the

Cargo Compartment and the Avionics

Compartment

Sheet 01

Sheet 02

(a) As shown in Fig. A-FBMAA Sheet 01, install the wire, using spares conduits

between Frame 37 and Frame 53.2, as shown on the wiring diagram, Fig. AFCBAA Sheet 01 and as given in the Hook-up Chart line :

- 1 (Refer to Fig. A-FCBAA Sheet 02) supplied in :

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Bundle F9000095227895

NOTE: The spares conduits is divided in two parts. The first parts go away

from Frame 40 to Frame 47 and the second parts go away from

Frame 48 to Frame 53.2

(b) Attach the wires with :

300 Tie-Cable NSA935401-03 Item 169

300 Tie-Cable NSA935401-08

300 Tie-Cable NSA935401-13

(2) Subtask 364033-831-017-001 - Modify the Wiring in the Main rack 800VU.

Work Zones and Access Panels

Zone Access/Work location

120 Work location Electrical panel 800VU

Manpower Resources

Manhours 4.00

Minimum number of person 2

Subtask elapsed time 2.00

Skills ELECTRICAL

Material necessary to do the job

Kit 364033A02R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

169 NSA935401-03 50 TIE

F9000095227895 BUNDLE

NSA935401-06 50 TIE

NSA935401-13 50 TIE

References

Aircraft Maintenance Manual (AMM) Task 36-11-34-000-802

Task 36-11-34-400-802

Fig. A-FCAAA

Modification of the Wiring in the Main

Rack 800VU

Sheet 01

Sheet 02

Sheet 03

Sheet 04

(a) Remove and retain the BMC (FIN 1HA1, 1HA2, 1HA3 and 1HA4) (Refer to AMM

Task 36-11-34-000-802).

(b) Remove the wires as shown on the wiring diagram Fig. A-FCAAA Sheet 01, and as

given in the Hook-up Chart lines :

- 1 thru 5 (Refer to Fig. A-FCAAA Sheet 04).

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(c) Install the wires as shown on the wiring diagrams, Fig. A-FCAAA Sheet 02 and Fig.

A-FCAAA Sheet 03 and as given in the Hook-up Chart lines :

- 9 thru 19 (Refer to Fig. A-FCAAA Sheet 04) supplied in :

Bundle F9000095227895

(d) Attach the wires with :

50 Tie-Cable NSA935401-03 Item 169

50 Tie-Cable NSA935401-06

50 Tie-Cable NSA935401-13

(e) Install the BMC (FIN 1HA1, 1HA2, 1HA3 and 1HA4) (Refer to AMM Task

36-11-34-400-802).

(3) Subtask 364033-831-001-001 - Remove the sensing elements and the supports

between FR39 and FR44.

Work Zones and Access Panels

Zone Access/Work location

190 Work location from Frame 39 to Frame 44

Manpower Resources

Manhours 4.00

Minimum number of person 1

Subtask elapsed time 4.00

Skills AIRFRAME

References

Aircraft Maintenance Manual (AMM) Task 36-22-17-000-801

Task 36-22-17-000-802

Fig. A-FBAAA

Removal of the Sensing Elements

between FR39 and FR55 on the LH side

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

(a) Remove :

Fig. A-FBAAA Sheet 01 Fig. A-FBAAA Sheet 02

(Refer to AMM Task 36-22-17-000-801 and AMM Task 36-22-17-000-802)

22 Screw Item (20) Discard

32 Washer Item (14) Discard

32 Clamp Item (86) Discard

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32 Sleeve Item (13) Discard

5 Screw Item (91) Discard

10 Spacer Item (16) Discard

5 Screw Item (21) Discard

2 Nut Item (15) Discard

FIN 97HF

1 Sensing Element 35610-2-255 Item (1) Discard

FIN 98HF

1 Sensing Element 35624-2-255 Item (2) Discard

4 Rivet Item (11) Discard

2 Support Item (10) Discard

(4) Subtask 364033-831-002-001 - Remove the sensing elements and the supports

between FR44 and FR51.

Work Zones and Access Panels

Zone Access/Work location

190 Work location from Frame 44 to Frame 51

Manpower Resources

Manhours 4.00

Minimum number of person 1

Subtask elapsed time 4.00

Skills AIRFRAME

References

Aircraft Maintenance Manual (AMM) Task 36-22-17-000-801

Fig. A-FBAAA

Removal of the Sensing Elements

between FR39 and FR55 on the LH side

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

(a) Remove :

Fig. A-FBAAA Sheet 01 Fig. A-FBAAA Sheet 03

(Refer to AMM Task 36-22-17-000-801)

18 Screw Item (21) Discard

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30 Washer Item (14) Discard

30 Clamp Item (86) Discard

30 Sleeve Item (13) Discard

18 Spacer Item (16) Discard

12 Screw Item (20) Discard

2 Nut Item (15) Discard

FIN 99HF

1 Sensing Element 35612-2-255 Item (3) Discard

FIN 100HF

1 Sensing Element 35605-2-255 Item (6) Discard

4 Rivet Item (11) Discard

2 Support Item (10) Discard

(5) Subtask 364033-831-003-001 - Remove the sensing elements and the supports

between FR51 and FR53.6.

Work Zones and Access Panels

Zone Access/Work location

190 Work location from Frame 51 to Frame 53.6

Manpower Resources

Manhours 4.00

Minimum number of person 1

Subtask elapsed time 4.00

Skills AIRFRAME

References

Aircraft Maintenance Manual (AMM) Task 36-22-17-000-801

Task 36-22-17-000-802

Fig. A-FBAAA

Removal of the Sensing Elements

between FR39 and FR55 on the LH side

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

(a) Remove :

Fig. A-FBAAA Sheet 01 Fig. A-FBAAA Sheet 04

(Refer to AMM Task 36-22-17-000-801 and AMM Task 36-22-17-000-802)

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18 Screw Item (21) Discard

37 Washer Item (14) Discard

37 Clamp Item (86) Discard

37 Sleeve Item (13) Discard

23 Spacer Item (16) Discard

16 Screw Item (20) Discard

1 Screw Item (93) Discard

1 Spacer Item (18) Discard

2 Screw Item (91) Discard

3 Nut Item (15) Discard

FIN 101HF

1 Sensing Element 35603-2-255 Item (4) Discard

FIN 102HF

1 Sensing Element 35600-2-255 Item (5) Discard

FIN 23HF

1 Sensing Element 35571-2-255 Item (7) Discard

6 Rivet Item (11) Discard

3 Support Item (10) Discard

(6) Subtask 364033-831-004-001 - Remove the sensing elements and the supports

between FR53.6 and FR55.

Work Zones and Access Panels

Zone Access/Work location

190 Work location from Frame 53.6 to Frame 55

Manpower Resources

Manhours 4.00

Minimum number of person 1

Subtask elapsed time 4.00

Skills AIRFRAME

References

Aircraft Maintenance Manual (AMM) Task 36-22-17-000-801

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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References

Fig. A-FBAAA

Removal of the Sensing Elements

between FR39 and FR55 on the LH side

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

(a) Remove :

Fig. A-FBAAA Sheet 01 Fig. A-FBAAA Sheet 05

(Refer to AMM Task 36-22-17-000-801)

19 Screw Item (20) Discard

27 Washer Item (14) Discard

27 Clamp Item (86) Discard

27 Sleeve Item (13) Discard

4 Screw Item (91) Discard

12 Spacer Item (16) Discard

4 Screw Item (21) Discard

2 Nut Item (15) Discard

FIN 24HF

1 Sensing Element 35580-2-255 Item (8) Discard

FIN 25HF

1 Sensing Element 35611-3-255 Item (9) Discard

2 Rivet Item (11) Discard

1 Support Item (10) Discard

(7) Subtask 364033-010-002-001 - If necessary, remove the ducts between FR53.5 and

FR53.6 for access.

Work Zones and Access Panels

Zone Access/Work location

150 Work location from Frame 53.5 to Frame 53.6

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Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills AIRFRAME

References

Aircraft Maintenance Manual (AMM) Task 36-12-41-000-801

Fig. A-FBBAA

Removal/Installation of the Ducts

between FR53.6 and FR53.7 on the LH

side (for Access)

Sheet 01

(a) Remove :

Fig. A-FBBAA

(Refer to AMM Task 36-12-41-000-801)

1 Duct assy Item (112) Retain

1 Duct assy Item (112) Retain

1 Duct assy Item (114) Retain

(8) Subtask 364033-831-005-001 - Drill a new hole in the structure between FR53.5 and

FR53.6.

Work Zones and Access Panels

Zone Access/Work location

150 Work location from Frame 53.5 to Frame 53.6

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills AIRFRAME

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Chemical Conversion

Coating Yellow Aluminum

13-002 As required

Anti-Corrosion Primer

(polyurethane)

16-001 As required

Polyurethane Finnish Paint 16-018 As required

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References

Fig. A-FBCAA

Drilling of a New Hole in the Structure

between FR53.5 and FR53.6 on the LH

side and Installation of Sensing

Elements

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

(a) Drill one hole on the structure between FR53.5 and FR53.6 to a diameter

comprised between 13.5mm (0.531in.) Min. and 13.7mm (0.539 in.) Max. as shown

on Fig. A-FBCAA.

(b) Do a spotfacing on the structure between FR53.5 and 53.6 to a diameter of 24mm

(0.944 in.) with a radius of 2mm (0.078in.)

NOTE: Be careful at the depth : 2mm (0.078 in.) Min. and 3mm (0.118 in.)

Max.

(c) Protect the hole and the spotfacing with :

Chemical

Conversion Coating

Yellow Aluminum

13-002 As required

Anti-Corrosion

Primer

(polyurethane)

16-001 As required

Polyurethane

Finnish Paint

16-018 As required

(9) Subtask 364033-831-006-001 - Install a new support for the routing of the sensing

elements between FR53.5 and FR53.6.

Work Zones and Access Panels

Zone Access/Work location

150 Work location from Frame 53.5 to Frame 53.6

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills NON SPECIFIC

Material necessary to do the job

Kit 364033A01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

96 F5392059300000 1 SUPPORT

97 ASNA2050DCJ3215 2 RIVET

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Reidentified part set REIDA01

ITEM NEW PART N ̊ KEYWORD ITEM OLD PART N ̊ SEE

NOTES

F0041196200000 BLANKET F2581571700000

F2582261900000

F0041196300000 BLANKET F2581566600000

F0041196400000 BLANKET F2581666600000

F0041196500000 BLANKET F2581677800000

F0041196600000 BLANKET F2581677900000

F0041196700000 BLANKET F2582242300000

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Adhesive Tape (insulation

Blanket Repair)

08-073 As required

Interfay Sealant 09-005A As required

Corrosion Inhibiting Fillet

Consistency

09-016B As required

References

Fig. A-FBFAA

Installation of a New Bracket between

FR53.5 and FR53.6

Sheet 01

Sheet 02

(a) Move the insulation blanket to get access to the modification area.

(b) Put the bracket Item 96 in position as shown on Fig. A-FBFAA.

(c) Drill two holes on the structure to a diameter comprised between 3.25mm (0.128in.)

and 3.35mm (0.132in.) to match the holes of the bracket Item 96.

Fig. A-FBFAA

(d) Cut the insulation blanket to permit the installation of the bracket Item 96.

NOTE: For the repair of the insulation blanket use :

Adhesive Tape

(insulation Blanket

Repair)

08-073 As required

(e) Re-identify the insulation blanket :

1 Blanket-Insulation F2581571700000

or

1 Blanket-Insulation F2582261900000

becomes

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1 Blanket-Insulation F0041196200000

or

1 Blanket-Insulation F2581566600000

becomes

1 Blanket-Insulation F0041196300000

or

1 Blanket-Insulation F2581666600000

becomes

1 Blanket-Insulation F0041196400000

or

1 Blanket-Insulation F2581677800000

becomes

1 Blanket-Insulation F0041196500000

or

1 Blanket-Insulation F2581677900000

becomes

1 Blanket-Insulation F0041196600000

or

1 Blanket-Insulation F2582242300000

becomes

1 Blanket-Insulation F0041196700000

(f) Install :

Fig. A-FBFAA

1 Support F5392059300000 Item 96

2 Rivet ASNA2050DCJ3215 Item 97

NOTE: To the interface of the new bracket and the structure, apply :

Interfay Sealant 09-005A As required

NOTE: Do a sealant bead around new parts with :

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Corrosion Inhibiting

Fillet Consistency

09-016B As required

NOTE: Wet install the fasteners with :

Interfay Sealant 09-005A As required

(g) Install the insulation blanket.

(10) Subtask 364033-410-001-001 - If removed, install the ducts between FR53.5 and

FR53.6.

Work Zones and Access Panels

Zone Access/Work location

150 Work location from Frame 53.5 to Frame 53.6

Manpower Resources

Manhours 2.00

Minimum number of person 1

Subtask elapsed time 2.00

Skills AIRFRAME

References

Aircraft Maintenance Manual (AMM) Task 36-12-41-400-801

Fig. A-FBBAA

Removal/Installation of the Ducts

between FR53.6 and FR53.7 on the LH

side (for Access)

Sheet 01

(a) Install :

(Refer to AMM Task 36-12-41-400-801)

1 Duct assy Item (112) Retained at

removal

1 Duct assy Item (112) Retained at

removal

1 Duct assy Item (114) Retained at

removal

(11) Subtask 364033-010-003-001 - If necessary, remove the ducts between FR43 and

FR45 for access.

Work Zones and Access Panels

Zone Access/Work location

190 Work location from Frame 43 to Frame 45

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 36-12-41-000-801

Fig. A-FBDAA

Removal/Installation of the Ducts

between FR44 and FR47 on the LH side

(for Access)

Sheet 01

(a) Remove :

(Refer to AMM Task 36-12-41-000-801)

1 Duct assy Item (115) Retain

1 Duct assy Item (116) Retain

(12) Subtask 364033-831-007-001 - Replace the web assy and the half clamp assy at

FR44.

Work Zones and Access Panels

Zone Access/Work location

190 Work location Frame 44

Manpower Resources

Manhours 3.00

Minimum number of person 1

Subtask elapsed time 3.00

Skills AIRFRAME

Material necessary to do the job

Kit 364033A01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

117 F5331591000200 1 WEB

118 F5331583500200 1 CLAMP

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Corrosion Inhibiting Fillet

Consistency

09-016B As required

Low Adhesion Polysulfide

Sealant

09-019B As required

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References

Fig. A-FBEAA

Replacement of the Web Assy at FR44

on the LH side

Sheet 01

Sheet 02

(a) Remove :

Fig. A-FBEAA

17 Screw Item (119) Retain

17 Washer Item (124) Retain

1 Strip cover assy Item (122) Retain

2 Screw Item (120) Retain

1 Half clamp assy F5331583500000 Item (118) Discard

1 Half clamp assy Item (121) Retain

1 Bracket Item (123) Retain

1 Web Assy F5331591000000 Item (117) Discard

NOTE: It is not necessary to remove completely the bracket Item (123).

(b) Install :

Fig. A-FBEAA

1 Web Assy F5331591000200 Item 117

1 Bracket Item (123) Retained at

removal

1 Half clamp assy Item (121) Retained at

removal

1 Half clamp assy F5331583500200 Item 118

2 Screw Item (120) Retained at

removal

1 Strip cover assy Item (122) Retained at

removal

17 Washer Item (124) Retained at

removal

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17 Screw Item (119) Retained at

removal

NOTE: Install the new web assy with :

Corrosion Inhibiting

Fillet Consistency

09-016B As required

and

Low Adhesion

Polysulfide Sealant

09-019B As required

(13) Subtask 364033-831-008-001 - Install the new brackets for the routing of the

sensing elements at FR44.

Work Zones and Access Panels

Zone Access/Work location

190 Work location Frame 44

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills AIRFRAME

Material necessary to do the job

Kit 364033A01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

97 ASNA2050DCJ3215 2 RIVET

98 F0041178800000 1 SUPPORT

99 F0041178800100 1 SUPPORT

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Interfay Sealant 09-005A As required

Corrosion Inhibiting Fillet

Consistency

09-016B As required

References

Fig. A-FBGAA

Installation of Two New Brackets at

FR44

Sheet 01

Sheet 02

(a) Put the brackets Item 98 and 99 in position as shown on Fig. A-FBGAA.

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(b) Drill two holes to a diameter comprised between 3.25mm (0.128in.) and 3.35mm

(0.132in.) as shown on Fig. A-FBGAA.

(c) Install :

1 Support F0041178800000 Item 98

1 Support F0041178800100 Item 99

2 Rivet ASNA2050DCJ3215 Item 97

NOTE: To the interface of the new bracket and the structure apply :

Interfay Sealant 09-005A As required

NOTE: Do a sealant bead around new parts with :

Corrosion Inhibiting

Fillet Consistency

09-016B As required

NOTE: Wet install the fasteners with :

Interfay Sealant 09-005A As required

(14) Subtask 364033-410-002-001 - If removed, install the ducts between FR43 and

FR45.

Work Zones and Access Panels

Zone Access/Work location

190 Work location from Frame 43 to Frame 45

Manpower Resources

Manhours 2.00

Minimum number of person 1

Subtask elapsed time 2.00

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 36-12-41-400-801

Fig. A-FBDAA

Removal/Installation of the Ducts

between FR44 and FR47 on the LH side

(for Access)

Sheet 01

(a) Install :

(Refer to AMM Task 36-12-41-400-801)

1 Duct assy Item (115) Retained at

removal

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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1 Duct assy Item (116) Retained at

removal

(15) Subtask 364033-831-009-001 - Install the sensing elements and the supports

between FR39 and FR44.

Work Zones and Access Panels

Zone Access/Work location

190 Work location from Frame 39 to Frame 44

Manpower Resources

Manhours 14.00

Minimum number of person 1

Subtask elapsed time 14.00

Skills AIRFRAME

Material necessary to do the job

Kit 364033A01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

10 NSA5543-00 30 CLAMP

11 ASNA0342T04-01 4 BOLT

13 NSA5539S 62 SLEEVE

14 ASNA2397-10L 34 WASHER

15 NSA5542-00 4 NUT

16 NSA5527-03-01 8 SPACER

18 NSA5527-03-11 6 SPACER

20 NAS6603-1 19 BOLT

21 NAS6603-9 8 BOLT

24 NAS6603-15 6 BOLT

29 NAS6603-2 2 BOLT

30 NSA5546-00 2 ANGLE

32 F1131031621700 2 PLACARD

33 F1131031623700 2 PLACARD

34 F1131031621800 1 PLACARD

35 F1131031623800 1 PLACARD

70 F3611548300000 1 SUPPORT

71 F3611548800000 1 SUPPORT

78 F3611549700000 1 SUPPORT

79 F3611549100000 1 SUPPORT

100 35606-2-255 1 SNSGELEM

101 35621-2-255 1 SNSGELEM

102 35620-2-255 1 SNSGELEM

113 35610-2-255 1 SNSGELEM

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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SERVICE BULLETIN

References

Fig. A-FBHAA

Installation of the New Sensing

Elements between FR39 and FR44 on

LH side

Sheet 01

Sheet 02

Sheet 03

Sheet 04

(a) Install the sensing elements and the supports between FR39 and FR40.2.

1 Install the supports between FR39 and FR40 :

1 Angle NSA5546-00 Item 30

2 Rivet-Blind ASNA0342T04-01 Item 11

8 Clamp NSA5543-00 Item 10

6 Spacer NSA5527-03-01 Item 16

2 Spacer NSA5527-03-11 Item 18

8 Washer ASNA2397-10L Item 14

6 Bolt NAS6603-9 Item 21

2 Bolt NAS6603-15 Item 24

2 Install the supports between FR40 and FR40.2 :

1 Support F3611549100000 Item 79

1 Support F3611549700000 Item 78

5 Clamp NSA5543-00 Item 10

1 Spacer NSA5527-03-01 Item 16

8 Washer ASNA2397-10L Item 14

1 Bolt NAS6603-9 Item 21

6 Bolt NAS6603-1 Item 20

2 Bolt NAS6603-2 Item 29

1 Angle NSA5546-00 Item 30

2 Rivet-Blind ASNA0342T04-01 Item 11

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 120

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SERVICE BULLETIN

3 Install the placards between FR39 and FR40.2 :

2 Placard F1131031621700 Item 32

2 Placard F1131031623700 Item 33

1 Placard F1131031621800 Item 34

1 Placard F1131031623800 Item 35

4 Install the sensing elements between FR39 and FR40.2 :

FIN 97HF

1 Sensing Element 35606-2-255 Item 100

FIN 302HF

1 Sensing Element 35610-2-255 Item 113

28 Sleeve-Protective NSA5539S Item 13

4 Nut NSA5542-00 Item 15

NOTE: Secure the nuts Item 15 with wire-lock MS20995C32 Item 27.

(b) Install the sensing elements and the supports between FR40.2 and FR44.

1 Install the supports between FR40.2 and FR44 :

1 Support F3611548300000 Item 70

1 Support F3611548800000 Item 71

17 Clamp NSA5543-00 Item 10

4 Spacer NSA5527-03-11 Item 18

1 Spacer NSA5527-03-01 Item 16

18 Washer ASNA2397-10L Item 14

13 Bolt NAS6603-1 Item 20

1 Bolt NAS6603-9 Item 21

4 Bolt NAS6603-15 Item 24

2 Install the sensing elements between FR40.2 and FR44 :

FIN 98HF

1 Sensing Element 35620-2-255 Item 102

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 121

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SERVICE BULLETIN

FIN 303HF

1 Sensing Element 35621-2-255 Item 101

34 Sleeve-Protective NSA5539S Item 13

(16) Subtask 364033-831-010-001 - Install the sensing elements and the supports

between FR44 and FR50.

Work Zones and Access Panels

Zone Access/Work location

190 Work location from Frame 44 to Frame 50

Manpower Resources

Manhours 14.00

Minimum number of person 1

Subtask elapsed time 14.00

Skills AIRFRAME

Material necessary to do the job

Kit 364033A01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

10 NSA5543-00 29 CLAMP

11 ASNA0342T04-01 4 BOLT

13 NSA5539S 58 SLEEVE

14 ASNA2397-10L 35 WASHER

15 NSA5542-00 8 NUT

16 NSA5527-03-01 11 SPACER

17 NSA5527-03-10 1 SPACER

18 NSA5527-03-11 3 SPACER

19 NAS6603-24 2 BOLT

20 NAS6603-1 14 BOLT

21 NAS6603-9 9 BOLT

23 NAS6603-16 1 BOLT

26 NAS6603-32 1 BOLT

29 NAS6603-2 8 BOLT

30 NSA5546-00 2 ANGLE

34 F1131031621800 1 PLACARD

35 F1131031623800 1 PLACARD

36 F1131031623900 2 PLACARD

37 F1131031621900 2 PLACARD

38 F1131031624000 2 PLACARD

39 F1131031622000 2 PLACARD

40 F1131031622100 1 PLACARD

41 F1131031624100 1 PLACARD

79 F3611549100000 4 SUPPORT

80 F3611549500000 1 SUPPORT

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 122

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SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

81 F3611549600000 1 SUPPORT

103 35618-2-255 2 SNSGELEM

105 35598-2-255 1 SNSGELEM

114 35597-2-255 1 SNSGELEM

References

Fig. A-FBJAA

Installation of the New Sensing

Elements between FR44 and FR50 on

LH side

Sheet 01

Sheet 02

Sheet 03

Sheet 04

(a) Install the sensing elements and the supports between FR44 and FR46.

1 Install the supports between FR44 and FR46 :

1 Support F3611549600000 Item 81

17 Clamp NSA5543-00 Item 10

9 Spacer NSA5527-03-01 Item 16

3 Spacer NSA5527-03-11 Item 18

21 Washer ASNA2397-10L Item 14

2 Bolt NAS6603-24 Item 19

5 Bolt NAS6603-1 Item 20

7 Bolt NAS6603-9 Item 21

1 Bolt NAS6603-16 Item 23

2 Bolt NAS6603-2 Item 29

2 Install the placards at FR44 :

1 Placard F1131031621800 Item 34

1 Placard F1131031623800 Item 35

1 Placard F1131031623900 Item 36

1 Placard F1131031621900 Item 37

3 Install the sensing elements between FR44 and FR46 :

FIN 99HF

1 Sensing Element 35618-2-255 Item 103

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 123

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SERVICE BULLETIN

FIN 304HF

1 Sensing Element 35618-2-255 Item 103

34 Sleeve-Protective NSA5539S Item 13

4 Nut NSA5542-00 Item 15

(b) Install the sensing elements and the supports between FR46 and FR50.

1 Install the supports between FR46 and FR50 :

2 Angle NSA5546-00 Item 30

4 Rivet-Blind ASNA0342T04-01 Item 11

1 Support F3611549500000 Item 80

4 Support F3611549100000 Item 79

12 Clamp NSA5543-00 Item 10

2 Spacer NSA5527-03-01 Item 16

1 Spacer NSA5527-03-10 Item 17

14 Washer ASNA2397-10L Item 14

9 Bolt NAS6603-1 Item 20

2 Bolt NAS6603-9 Item 21

1 Bolt NAS6603-32 Item 26

6 Bolt NAS6603-2 Item 29

2 Install the placards between FR46 and FR50 :

1 Placard F1131031623900 Item 36

1 Placard F1131031621900 Item 37

2 Placard F1131031624000 Item 38

2 Placard F1131031622000 Item 39

1 Placard F1131031622100 Item 40

1 Placard F1131031624100 Item 41

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 124

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SERVICE BULLETIN

3 Install the sensing elements between FR46 and FR50 :

FIN 100HF

1 Sensing Element 35597-2-255 Item 114

FIN 305HF

1 Sensing Element 35598-2-255 Item 105

24 Sleeve-Protective NSA5539S Item 13

4 Nut NSA5542-00 Item 15

NOTE: Secure the nuts Item 15 with wire-lock MS20995C32 Item 27.

(17) Subtask 364033-831-011-001 - Install the sensing elements and the supports

between FR50 and FR53.6.

Work Zones and Access Panels

Zone Access/Work location

190 Work location from Frame 50 to Frame 53.6

Manpower Resources

Manhours 21.00

Minimum number of person 1

Subtask elapsed time 21.00

Skills AIRFRAME

Material necessary to do the job

Kit 364033A01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

10 NSA5543-00 37 CLAMP

11 ASNA0342T04-01 6 BOLT

13 NSA5539S 74 SLEEVE

14 ASNA2397-10L 51 WASHER

15 NSA5542-00 6 NUT

16 NSA5527-03-01 16 SPACER

18 NSA5527-03-11 1 SPACER

20 NAS6603-1 23 BOLT

21 NAS6603-9 16 BOLT

22 NSA5527-03-15 1 SPACER

24 NAS6603-15 1 BOLT

25 NSA5545-00 1 ANGLE

28 NAS6603-12 1 BOLT

29 NAS6603-2 10 BOLT

30 NSA5546-00 2 ANGLE

40 F1131031622100 1 PLACARD

41 F1131031624100 1 PLACARD

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 125

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SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

42 F1131031622200 2 PLACARD

43 F1131031624200 2 PLACARD

44 F1131031620400 2 PLACARD

45 F1131031624300 2 PLACARD

70 F3611548300000 1 SUPPORT

72 F3611548700000 1 SUPPORT

73 F3611548500000 1 SUPPORT

74 F3611548900000 1 SUPPORT

75 F3611548400000 1 SUPPORT

76 F3611548200000 1 SUPPORT

77 F3611548620000 1 SUPPORT

79 F3611549100000 3 SUPPORT

82 F3611549400000 1 SUPPORT

83 F3611549800000 1 SUPPORT

84 F3611549300000 1 SUPPORT

104 35567-3-255 1 SNSGELEM

106 35595-2-255 3 SNSGELEM

107 35596-2-255 1 SNSGELEM

108 35568-4-255 1 SNSGELEM

References

Fig. A-FBKAA

Installation of the New Sensing

Elements between FR50 and FR53.6 on

LH side

Sheet 01

Sheet 02

Sheet 03

Sheet 04

(a) Install the sensing elements and the supports between FR50 and FR53.2.

1 Install the supports between FR50 and FR53.2 :

1 Support F3611548700000 Item 72

1 Support F3611548400000 Item 75

1 Support F3611549400000 Item 82

1 Angle NSA5546-00 Item 30

2 Rivet-Blind ASNA0342T04-01 Item 11

13 Clamp NSA5543-00 Item 10

7 Spacer NSA5527-03-01 Item 16

16 Washer ASNA2397-10L Item 14

9 Bolt NAS6603-1 Item 20

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 126

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SERVICE BULLETIN

7 Bolt NAS6603-9 Item 21

2 Install the placards between FR50 and FR53.2 :

1 Placard F1131031622100 Item 40

1 Placard F1131031624100 Item 41

1 Placard F1131031622200 Item 42

1 Placard F1131031624200 Item 43

3 Install the sensing elements between FR50 and FR53.2 :

FIN 101HF

1 Sensing Element 35595-2-255 Item 106

FIN 306HF

1 Sensing Element 35595-2-255 Item 106

26 Sleeve-Protective NSA5539S Item 13

2 Nut NSA5542-00 Item 15

NOTE: Secure the nuts Item 15 with wire-lock MS20995C32 Item 27.

(b) Install the sensing elements and the supports between FR53.2 and FR53.6.

1 Install the supports between FR53.2 and FR53.6 :

1 Support F3611548300000 Item 70

1 Support F3611548500000 Item 73

1 Support F3611548900000 Item 74

1 Support F3611548200000 Item 76

1 Support F3611548620000 Item 77

3 Support F3611549100000 Item 79

1 Support F3611549800000 Item 83

1 Support F3611549300000 Item 84

1 Angle NSA5545-00 Item 25

1 Angle NSA5546-00 Item 30

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 127

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SERVICE BULLETIN

4 Rivet-Blind ASNA0342T04-01 Item 11

24 Clamp NSA5543-00 Item 10

9 Spacer NSA5527-03-01 Item 16

1 Spacer NSA5527-03-11 Item 18

1 Spacer NSA5527-03-15 Item 22

35 Washer ASNA2397-10L Item 14

14 Bolt NAS6603-1 Item 20

9 Bolt NAS6603-9 Item 21

1 Bolt NAS6603-15 Item 24

1 Bolt NAS6603-12 Item 28

10 Bolt NAS6603-2 Item 29

2 Install the placards between FR53.2 and FR53.6 :

1 Placard F1131031622200 Item 42

1 Placard F1131031624200 Item 43

2 Placard F1131031620400 Item 44

2 Placard F1131031624300 Item 45

3 Install the sensing elements between FR53.2 and FR53.6 :

FIN 102HF

1 Sensing Element 35595-2-255 Item 106

FIN 307HF

1 Sensing Element 35596-2-255 Item 107

FIN 23HF

1 Sensing Element 35568-4-255 Item 108

FIN 308HF

1 Sensing Element 35567-3-255 Item 104

48 Sleeve-Protective NSA5539S Item 13

4 Nut NSA5542-00 Item 15

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 128

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SERVICE BULLETIN

NOTE: Secure the nuts Item 15 with wire-lock MS20995C32 Item 27.

(18) Subtask 364033-831-012-001 - Install the sensing elements and the supports

between FR53.6 and FR55.

Work Zones and Access Panels

Zone Access/Work location

190 Work location from Frame 53.6 to Frame 55

Manpower Resources

Manhours 14.00

Minimum number of person 1

Subtask elapsed time 14.00

Skills AIRFRAME

Material necessary to do the job

Kit 364033A01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

10 NSA5543-00 27 CLAMP

11 ASNA0342T04-01 2 BOLT

13 NSA5539S 55 SLEEVE

14 ASNA2397-10L 32 WASHER

15 NSA5542-00 2 NUT

16 NSA5527-03-01 6 SPACER

17 NSA5527-03-10 2 SPACER

18 NSA5527-03-11 5 SPACER

20 NAS6603-1 17 BOLT

21 NAS6603-9 1 BOLT

26 NAS6603-32 2 BOLT

29 NAS6603-2 2 BOLT

30 NSA5546-00 1 ANGLE

70 F3611548300000 1 SUPPORT

79 F3611549100000 1 SUPPORT

85 NSA5549-90 2 CONNECTR

86 NSA5538-00 3 CLAMP

87 NAS6603-17 5 BOLT

88 F1131031620500 1 PLACARD

89 F1131031624400 1 PLACARD

90 F1131031620600 1 PLACARD

91 F1131031624500 1 PLACARD

93 F3611549200095 1 SUPPORT

94 NAS6603-10 5 BOLT

95 F3611549000000 1 SUPPORT

109 35597-3-255 1 SNSGELEM

110 35587-2-255 1 SNSGELEM

111 35627-2-255 1 SNSGELEM

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 129

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SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

112 35625-2-255 1 SNSGELEM

References

Fig. A-FBLAA

Installation of the New Sensing

Elements between FR53.6 and FR55 on

LH side

Sheet 01

Sheet 02

Sheet 03

Sheet 04

(a) Install the sensing elements and the supports between FR53.6 and FR55.

1 Install the supports between FR53.6 and FR55 :

1 Support F3611548300000 Item 70

1 Support F3611549100000 Item 79

1 Support F3611549200095 Item 93

1 Support F3611549000000 Item 95

1 Angle NSA5546-00 Item 30

2 Rivet-Blind ASNA0342T04-01 Item 11

27 Clamp NSA5543-00 Item 10

3 Clamp NSA5538-00 Item 86

6 Spacer NSA5527-03-01 Item 16

2 Spacer NSA5527-03-10 Item 17

5 Spacer NSA5527-03-11 Item 18

32 Washer ASNA2397-10L Item 14

17 Bolt NAS6603-1 Item 20

1 Bolt NAS6603-9 Item 21

2 Bolt NAS6603-32 Item 26

2 Bolt NAS6603-2 Item 29

5 Bolt NAS6603-17 Item 87

5 Bolt NAS6603-10 Item 94

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 130

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SERVICE BULLETIN

2 Install the placards between FR53.6 and FR55 :

1 Placard F1131031620500 Item 88

1 Placard F1131031624400 Item 89

1 Placard F1131031620600 Item 90

1 Placard F1131031624500 Item 91

3 Install the sensing elements between FR53.6 and FR55 :

FIN 24HF

1 Sensing Element 35597-3-255 Item 109

FIN 311HF

1 Sensing Element 35587-2-255 Item 110

FIN 25HF

1 Sensing Element 35627-2-255 Item 111

FIN 312HF

1 Sensing Element 35625-2-255 Item 112

2 Nut NSA5542-00 Item 15

2 Connector NSA5549-90 Item 85

55 Sleeve-Protective NSA5539S Item 13

NOTE: Secure the nuts Item 15 with wire-lock MS20995C32 Item 27.

(19) Subtask 364033-010-004-001 - If necessary, remove the ducts between FR39 and

FR40 for access.

Work Zones and Access Panels

Zone Access/Work location

190

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills AIRFRAME

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-010-801

Fig. A-FBPAA

Removal/Installation of the Ducts

Between FR39 and FR40 for Access

Sheet 01

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 131

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SERVICE BULLETIN

(a) Remove :

Fig. A-FBPAA

(Refer to AMM Task 21-20-00-010-801)

1 Duct assy Item (125) Retain

1 Duct assy Item (126) Retain

1 Duct assy Item (127) Retain

(20) Subtask 364033-831-013-001 - Install the new supports for the new harness

between FR39.1 and FR39.2.

Work Zones and Access Panels

Zone Access/Work location

190

Manpower Resources

Manhours 3.00

Minimum number of person 1

Subtask elapsed time 3.00

Skills AIRFRAME

Material necessary to do the job

Kit 364033A01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

63 ASNA2327-3-8 2 SUPPORT

64 F5391094700095 1 PLATE

65 NSA5456-3-8 1 SUPPORT

97 ASNA2050DCJ3215 14 RIVET

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Corrosion Inhibiting Brush

Consistency

09-013B As required

References

Fig. A-FBNAA

Installation of the Supports for the New

Harness

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 132

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SERVICE BULLETIN

(a) At FR39.1, remove a support between STGR 37 and STGR 38.

Fig. A-FBNAA Sheet 02 and Fig. A-FBNAA Sheet 03

1 Remove :

2 Rivet Item (97) Discard

1 Support Item (88) Retain

2 Install :

2 Rivet ASNA2050DCJ3215 Item 97

NOTE: Wet install the fasteners with :

Corrosion Inhibiting

Brush Consistency

09-013B As required

(b) At FR39.1, install a support between STGR 37 and STGR 38.

Fig. A-FBNAA Sheet 02 and Fig. A-FBNAA Sheet 03

1 Put the support Item (88) in position as shown on Fig. A-FBNAA Sheet 03.

2 Drill two holes on the structure to a diameter comprised between 3.25mm

(0.128in.) and 3.35mm (0.132in.) to match the holes of the support Item (88).

3 Install :

1 Support Item (88) Retained at

removal

2 Rivet ASNA2050DCJ3215 Item 97

NOTE: Wet install the fasteners with :

Corrosion Inhibiting

Brush Consistency

09-013B As required

(c) At FR39.2, install a plate between STGR 46 and STGR 47.

Fig. A-FBNAA Sheet 02 and Fig. A-FBNAA Sheet 04

1 Remove :

2 Rivet Item (97) Discard

1 Support Item (89) Retain

2 Put the plate Item 64 in position as shown on Fig. A-FBNAA Sheet 04.

3 Drill one hole on the plate Item 64 to a diameter comprised between 3.25mm

(0.128in.) and 3.35mm (0.132in.) to match the hole of the structure.

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 133

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SERVICE BULLETIN

4 Drill three holes on the structure to a diameter comprised between 3.25mm

(0.128in.) and 3.35mm (0.132in.) to match the holes of the plate Item (64).

5 Install :

1 Plate F5391094700095 Item 64

4 Rivet ASNA2050DCJ3215 Item 97

NOTE: Wet install the fasteners with :

Corrosion Inhibiting

Brush Consistency

09-013B As required

(d) At FR39.2, install two supports between STGR46 and STGR48.

Fig. A-FBNAA Sheet 02 and Fig. A-FBNAA Sheet 04

1 Put the supports Item 63 in position as shown on Fig. A-FBNAA Sheet 04.

2 Drill four holes on the structure to a diameter comprised between 3.25mm

(0.128in.) and 3.35mm (0.132in.) to match the holes of the supports Item 63.

3 Install :

2 Support ASNA2327-3-8 Item 63

4 Rivet ASNA2050DCJ3215 Item 97

NOTE: Wet install the fasteners with :

Corrosion Inhibiting

Brush Consistency

09-013B As required

(e) At FR39.1, install a support between STGR 39 and STGR 40.

Fig. A-FBNAA Sheet 02 and Fig. A-FBNAA Sheet 05

1 Put the support Item 65 in position as shown on Fig. A-FBNAA Sheet 05.

2 Drill two holes on the structure to a diameter comprised between 3.25mm

(0.128in.) and 3.35mm (0.132in.) to match the holes of the support Item 65.

3 Install :

1 Support NSA5456-3-8 Item 65

2 Rivet ASNA2050DCJ3215 Item 97

NOTE: Wet install the fasteners with :

Corrosion Inhibiting

Brush Consistency

09-013B As required

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 134

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SERVICE BULLETIN

(21) Subtask 364033-831-014-001 - Install the Interconnecting Electrical Wire FIN 309HF

and 310HF, between the sensing elements.

Work Zones and Access Panels

Zone Access/Work location

150

Manpower Resources

Manhours 3.00

Minimum number of person 1

Subtask elapsed time 3.00

Skills NON SPECIFIC

Material necessary to do the job

Kit 364033A02R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

14 ASNA2397-10L 1 WASHER

18 NSA5527-03-11 1 SPACER

92 NSA57304-643ADL 1 PLATE

155 NSA5516-04ND 1 CLAMP

168 NAS1801-3-22 1 SCREW

169 NSA935401-03 8 TIE

174 35301-74 1 CABLE

175 35301-75 2 CABLE

182 NSA5050-4 1 NUT

F1131031521900 1 PLACARD

F1131031522000 1 PLACARD

F9000095227895 BUNDLE

F9100095005595 1 PLACARD

References

Fig. A-FBCAA

Drilling of a New Hole in the Structure

between FR53.5 and FR53.6 on the LH

side and Installation of Sensing

Elements

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Fig. A-FCCAA

Installation of the Wiring of the New

Sensing Elements

Sheet 01

Sheet 02

(a) Put in position :

FIN 309HF

1 Cable-Electrical

Interconnecting

35301-74 Item 174

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 135

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SERVICE BULLETIN

(b) Put in position :

FIN 310HF

1 Cable-Electrical

Interconnecting

35301-75 Item 175

(c) Install the splice FIN 3593VS (PN E0360RK1816) between the FIN 309HF and the

FIN 310HF, supplied in :

Bundle F9000095227895

(d) Identify the splice FIN 3593VS with the identification sleeves and the identification

label supplied in :

1 Placard F9100095005595

and

Bundle F9000095227895

(e) On the fuselage close to the plugs, identify the FIN 309HF and the FIN 310HF with

:

1 Placard F1131031521900

and

1 Placard F1131031522000

(f) Identify the wire No. 3622-0543 of the FIN 310HF and the wire No. 3622-0544 of

the FIN 309HF with the identification sleeves supplied in :

1 Placard F9100095005595

(g) Modify the splice FIN 3503VS :

1 Before any disconnection, record the wires number associated to the FIN

137HF and the FIN 138HF.

2 Remove the splice FIN 3503VS between the FIN 137HF and the FIN 138HF :

FIN 3503VS

1 Splice Discard

NOTE: Retain the identification sleeves and the identification label of

the 3503VS and of the wires associated to the FIN 137HF and

the FIN 138HF.

3 Remove :

FIN 137HF

1 Cable-Electrical

Interconnecting

35301-74 Item (174) Discard

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 136

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SERVICE BULLETIN

4 Maintain in position :

FIN 138HF

1 Cable-Electrical

Interconnecting

35301-75 Item (175)

5 Put in position :

FIN 137HF

1 Cable-Electrical

Interconnecting

35301-75 Item 175

6 Install the new splice FIN 3503VS (PN E0360RK1816) between the FIN

137HF and the FIN 138HF, supplied in :

Bundle F9000095227895

NOTE: Identify the splice FIN 3503VS with the identification sleeves

and the identification label retained at removal.

NOTE: In accordance to the wires connections recorded at removal,

identify the wires associated to the FINs 137HF and 138HF

with the retained identification sleeves.

(h) Between Frame 53.5 and Frame 53.6 and as shown in Fig. A-FBCAA Sheet 01 and

Fig. A-FBCAA Sheet 03, install the FINs 137HF and 138HF and the FINs 309HF

and 310HF (spliced previously) with :

1 Spacer NSA5527-03-11 Item 18

1 Clamp NSA5516-04ND Item (155) Retained at

removal

1 Clamp NSA5516-04ND Item 155

1 Washer ASNA2397-10L Item 14

1 Screw NAS1801-3-22 Item 168

and attach it with :

8 Tie-Cable NSA935401-03 Item 169

NOTE: After connection, secure the FINs 137HF and 138HF and the FINs

309HF and 310HF with Wire-lock MS20995C32 item 27, (Refer to

Fig. A-FBCAA Sheet 05).

(i) Secure the FIN 310HF :

Refer to Fig. A-FBCAA Sheet 04

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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1 Remove :

1 Nut Discard

2 Install :

1 Plate-Attachment NSA57304-643ADL Item 92

With :

1 Nut NSA5050-4 Item 182

3 Secure the new nut and the FIN 310HF with wire-lock MS20995C32 item 27,

(Refer to Fig. A-FBCAA Sheet 05).

(22) Subtask 364033-831-015-001 - Install the new Harness 2SG.

Work Zones and Access Panels

Zone Access/Work location

190

Manpower Resources

Manhours 26.00

Minimum number of person 2

Subtask elapsed time 13.00

Skills NON SPECIFIC

Material necessary to do the job

Kit 364033A02R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

14 ASNA2397-10L 4 WASHER

16 NSA5527-03-01 2 SPACER

18 NSA5527-03-11 1 SPACER

22 NSA5527-03-15 1 SPACER

131 NSA935808-03 24 WASHER

134 NSA935807-16 1 CLAMP

135 NSA935807-20 1 CLAMP

141 NSA5527-03-02 3 SPACER

150 NSA935807-04 30 CLAMP

151 NSA5159-17 19 STUD

152 NSA5527-03-08 19 SPACER

153 NSA935808-01 13 WASHER

154 NSA5050-3 28 NUT

157 NSA5159-10 1 STUD

158 NAS1801-3-9 4 SCREW

159 NAS1801-3-8 2 SCREW

163 NSA5159-27 5 STUD

165 NSA5527-03-05 1 SPACER

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

166 NAS1801-3-12 4 SCREW

167 NAS1801-3-10 3 SCREW

170 MS21042-3 4 NUT

171 NAS1801-3-17 2 SCREW

172 NAS1149F0332P 2 WASHER

173 NSA5527-03-12 6 SPACER

174 35301-74 1 CABLE

176 NSA5516-21ND 5 CLAMP

177 NSA5516-22ND 5 CLAMP

178 NSA5516-23ND 5 CLAMP

179 NSA5516-07ND 2 CLAMP

180 NSA5516-08ND 2 CLAMP

181 NSA5516-10ND 2 CLAMP

183 NSA934710E20 3 SPRING

184 NSA934710T11 2 FITTING

E0432A04 20 (M) CONDUIT

F1131031522100 1 PLACARD

F9000095227895 BUNDLE

References

Elec. Std. Practices Manual (ESPM) 20-43-42

Fig. A-FBMAA

Installation of the New Harness 2SG

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

Sheet 09

Sheet 10

Sheet 11

Sheet 12

Sheet 13

Sheet 14

Sheet 15

Sheet 16

Sheet 17

Sheet 18

Sheet 19

Sheet 20

Sheet 21

Sheet 22

Fig. A-FCCAA

Installation of the Wiring of the New

Sensing Elements

Sheet 01

Sheet 02

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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SERVICE BULLETIN

(a) Install supports of new routing between 302HF located on the left hand side at

stringer 36 and Frame 40 and the 3520VP located on the right hand side at Frame

39.1 :

1 On the left hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03, Fig. A-FBMAA Sheet 04, Fig. A-FBMAA Sheet 05 and Fig. AFBMAA Sheet 06, along the Frame 39.1 and between Frame 39.1 and Frame

39.2, remove :

a For Section A-A :

7 Screw Item (130) Discard

7 Washer Item (131) Discard

7 Clamp Item (150) Retain

2 On the left hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03, Fig. A-FBMAA Sheet 04, Fig. A-FBMAA Sheet 05 and Fig. AFBMAA Sheet 06, along the Frame 39.1 and between Frame 39.1 and Frame

39.2, install :

a For Section B-B :

7 Stud NSA5159-17 Item 151

7 Clamp Item (150) Retained at

removal

7 Spacer NSA5527-03-08 Item 152

7 Clamp NSA935807-04 Item 150

7 Washer NSA935808-03 Item 131

7 Nut NSA5050-3 Item 154

b For Section C-C :

1 Stud NSA5159-17 Item 151

1 Clamp NSA935807-04 Item 150

1 Spacer NSA5527-03-08 Item 152

1 Clamp NSA935807-04 Item 150

1 Washer NSA935808-03 Item 131

1 Nut NSA5050-3 Item 154

NOTE: Install this hardware on the support Item 65 installed

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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previously.

3 On the left hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03, Fig. A-FBMAA Sheet 04, Fig. A-FBMAA Sheet 05 , Fig. A-FBMAA

Sheet 07, Fig. A-FBMAA Sheet 08 and Fig. A-FBMAA Sheet 09, along the

Frame 39.1 and between Stringer 39 and 40, remove :

a For Section F-F :

1 Screw Item (130) Discard

1 Washer Item (131) Discard

1 Clamp Item (150) Retain

b For Section G-G :

1 Screw Item (132) Discard

1 Washer Item (133) Discard

1 Clamp Item (155) Retain

4 On the left hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03, Fig. A-FBMAA Sheet 04, Fig. A-FBMAA Sheet 05 , Fig. A-FBMAA

Sheet 07, Fig. A-FBMAA Sheet 08 and Fig. A-FBMAA Sheet 09, along the

Frame 39.1 and between Stringer 39 and 40, install :

a For Section H-H :

1 Stud NSA5159-17 Item 151

1 Clamp Item (150) Retained at

removal

1 Spacer NSA5527-03-08 Item 152

1 Clamp NSA935807-04 Item 150

1 Washer NSA935808-03 Item 131

1 Nut NSA5050-3 Item 154

b For Section J-J :

1 Stud NSA5159-17 Item 151

1 Clamp Item (155) Retained at

removal

1 Spacer NSA5527-03-08 Item 152

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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1 Clamp NSA935807-04 Item 150

1 Washer NSA935808-03 Item 131

1 Nut NSA5050-3 Item 154

5 On the left hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 09, along the Frame 39.1 and between

Stringer 40 and 43, remove for detail F :

2 Screw Item (136) Discard

2 Washer Item (137) Discard

2 Clamp Item (135) Retain

2 Clamp Item (134) Retain

6 On the left hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 09, along the Frame 39.1 and between

Stringer 40 and 43, install for detail G :

2 Stud NSA5159-17 Item 151

2 Clamp Item (134) Retained at

removal

2 Clamp Item (135) Retained at

removal

2 Spacer NSA5527-03-08 Item 152

2 Clamp NSA935807-04 Item 150

2 Washer NSA935808-03 Item 131

2 Nut NSA5050-3 Item 154

7 On the left hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03, Fig. A-FBMAA Sheet 10 and Fig. A-FBMAA Sheet 11, along the

Frame 39.1 and between Stringers 44 and 45, remove :

a For Section K-K :

1 Nut Item (154) Discard

1 Washer Item (153) Discard

1 Clamp Item (138) Retain

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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SERVICE BULLETIN

1 Spacer Item (152) Retain

1 Clamp Item (135) Retain

1 Clamp Item (134) Retain

1 Stud Item (151) Retain

Or

1 Nut Item (154) Discard

1 Washer Item (153) Discard

1 Clamp Item (138) Retain

1 Clamp Item (139) Retain

1 Spacer Item (152) Discard

1 Clamp Item (135) Retain

1 Clamp Item (134) Retain

1 Stud Item (151) Discard

8 On the left hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03, Fig. A-FBMAA Sheet 10 and Fig. A-FBMAA Sheet 11, along the

Frame 39.1 and between Stringers 44 and 45, install :

a For Section M-M :

1 Stud Item (151) Retained at

removal

1 Clamp Item (134) Retained at

removal

1 Clamp Item (135) Retained at

removal

1 Spacer Item (152) Retained at

removal

1 Clamp Item (138) Retained at

removal

1 Clamp NSA935807-04 Item 150

1 Washer NSA935808-03 Item 131

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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1 Nut NSA5050-3 Item 154

Or

1 Stud NSA5159-27 Item 163

1 Clamp Item (134) Retained at

removal

1 Clamp Item (135) Retained at

removal

2 Spacer NSA5527-03-12 Item 173

1 Clamp Item (139) Retained at

removal

1 Clamp Item (138) Retained at

removal

1 Clamp NSA935807-04 Item 150

1 Washer NSA935808-03 Item 131

1 Nut NSA5050-3 Item 154

9 On the left hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03, Fig. A-FBMAA Sheet 10 and Fig. A-FBMAA Sheet 12, along the

Frame 39.1 and between Stringers 44 and 45, remove :

a For Section L-L :

1 Screw Item (130) Discard

1 Washer Item (153) Discard

1 Clamp Item (135) Retain

1 Clamp Item (134) Retain

10 On the left hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03, Fig. A-FBMAA Sheet 10 and Fig. A-FBMAA Sheet 12, along the

Frame 39.1 and between Stringers 44 and 45, install :

a For Section N-N :

1 Stud NSA5159-17 Item 151

1 Clamp Item (134) Retained at

removal

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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1 Clamp Item (135) Retained at

removal

1 Spacer NSA5527-03-08 Item 152

1 Clamp NSA935807-04 Item 150

1 Washer NSA935808-03 Item 131

1 Nut NSA5050-3 Item 154

11 On the left hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03, Fig. A-FBMAA Sheet 13 and Fig. A-FBMAA Sheet 14, along the

Frame 39.1 and between Stringers 46 and 48, remove :

a For Section P-P :

1 Nut Item (154) Discard

1 Washer Item (153) Discard

1 Clamp Item (139) Retain

1 Spacer Item (152) Retain

1 Clamp Item (135) Retain

1 Clamp Item (134) Retain

1 Stud Item (151) Discard

Or

1 Nut Item (154) Discard

1 Washer Item (153) Discard

1 Clamp Item (138) Retain

1 Clamp Item (139) Retain

1 Spacer Item (152) Discard

1 Clamp Item (135) Retain

1 Clamp Item (134) Retain

1 Stud Item (151) Discard

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 145

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12 On the left hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03, Fig. A-FBMAA Sheet 13 and Fig. A-FBMAA Sheet 14, along the

Frame 39.1 and between Stringers 46 and 48, install :

a For Section R-R :

1 Stud NSA5159-17 Item 151

1 Clamp Item (134) Retained at

removal

1 Clamp Item (135) Retained at

removal

1 Spacer Item (152) Retained at

removal

1 Clamp Item (139) Retained at

removal

1 Clamp NSA935807-04 Item 150

1 Washer NSA935808-03 Item 131

1 Nut NSA5050-3 Item 154

Or

1 Stud NSA5159-27 Item 163

1 Clamp Item (134) Retained at

removal

1 Clamp Item (135) Retained at

removal

2 Spacer NSA5527-03-12 Item 173

1 Clamp Item (139) Retained at

removal

1 Clamp Item (138) Retained at

removal

1 Clamp NSA935807-04 Item 150

1 Washer NSA935808-03 Item 131

1 Nut NSA5050-3 Item 154

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 146

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13 On the left hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03, Fig. A-FBMAA Sheet 13 and Fig. A-FBMAA Sheet 15, along the

Frame 39.1 and between Stringers 46 and 48, remove :

a For Section Q-Q :

1 Nut Item (154) Discard

1 Washer Item (153) Discard

1 Clamp Item (135) Retain

1 Spacer Item (152) Retain

1 Clamp Item (134) Retain

1 Clamp Item (139) Retain

1 Stud Item (151) Retain

Or

1 Nut Item (154) Discard

1 Washer Item (153) Discard

1 Clamp Item (138) Retain

1 Clamp Item (135) Retain

1 Spacer Item (152) Discard

1 Clamp Item (134) Retain

1 Clamp Item (139) Retain

1 Stud Item (144) Discard

14 On the left hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03, Fig. A-FBMAA Sheet 13 and Fig. A-FBMAA Sheet 15, along the

Frame 39.1 and between Stringers 46 and 48, install :

a For Section S-S :

1 Stud Item (151) Retained at

removal

1 Clamp NSA935807-04 Item 150

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 147

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SERVICE BULLETIN

1 Clamp Item (134) Retained at

removal

1 Spacer Item (152) Retained at

removal

1 Clamp Item (139) Retained at

removal

1 Clamp Item (135) Retained at

removal

1 Washer NSA935808-01 Item 153

1 Nut NSA5050-3 Item 154

Or

1 Stud NSA5159-27 Item 163

1 Clamp NSA935807-04 Item 150

1 Clamp Item (134) Retained at

removal

2 Spacer NSA5527-03-12 Item 173

1 Clamp Item (139) Retained at

removal

1 Clamp Item (138) Retained at

removal

1 Clamp Item (135) Retained at

removal

1 Washer NSA935808-01 Item 153

1 Nut NSA5050-3 Item 154

15 On the left hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 16, along the Frame 39.1 and between

Stringers 49 and 52, remove for detail K :

2 Screw Item (132) Discard

2 Washer Item (153) Discard

2 Clamp Item (138) Retain

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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16 On the left hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 16, along the Frame 39.1 and between

Stringers 49 and 52, install for detail L :

2 Stud NSA5159-17 Item 151

2 Clamp Item (138) Retained at

removal

2 Spacer NSA5527-03-08 Item 152

2 Clamp NSA935807-04 Item 150

2 Washer NSA935808-03 Item 131

2 Nut NSA5050-3 Item 154

17 On the left hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 17, along the Frame 39.1 and between

Stringers 52 and 54, remove for Section T-T :

1 Nut Item (154) Discard

1 Washer Item (153) Discard

1 Clamp Item (138) Retain

1 Spacer Item (141) Retain

1 Clamp Item (138) Retain

1 Stud Item (140) Retain

18 On the left hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 17, along the Frame 39.1 and between

Stringers 52 and 54, install for Section U-U :

1 Stud Item (140) Retained at

removal

1 Clamp Item (138) Retained at

removal

1 Spacer Item (141) Retained at

removal

1 Clamp Item (138) Retained at

removal

1 Clamp NSA935807-04 Item 150

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 149

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SERVICE BULLETIN

1 Washer NSA935808-03 Item 131

1 Nut NSA5050-3 Item 154

19 On the right hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 18, along the Frame 39.1 and near the

Stringers 54, remove for detail N :

1 Screw Item (142) Discard

1 Washer Item (153) Discard

1 Clamp Item (138) Retain

20 On the right hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 18, along the Frame 39.1 and near the

Stringers 54, install for detail P :

1 Stud NSA5159-17 Item 151

1 Clamp Item (138) Retained at

removal

1 Spacer NSA5527-03-08 Item 152

1 Clamp NSA935807-04 Item 150

1 Washer NSA935808-03 Item 131

1 Nut NSA5050-3 Item 154

21 On the right hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 18, along the Frame 39.1 and between

Stringers 54 and 48, remove for detail Q :

3 Screw Item (142) Discard

3 Washer Item (153) Discard

3 Clamp Item (138) Retain

22 On the right hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 18, along the Frame 39.1 and between

Stringers 54 and 48, install for detail R :

3 Clamp NSA935807-04 Item 150

3 Clamp Item (138) Retained at

removal

3 Washer NSA935808-01 Item 153

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 150

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SERVICE BULLETIN

3 Screw NAS1801-3-9 Item 158

23 On the right hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 18, between the Frame 39.1 and Frame

39.2 and between Stringers 48 and 46, install for detail S :

2 Clamp NSA935807-04 Item 150

2 Washer NSA935808-03 Item 131

2 Screw NAS1801-3-8 Item 159

NOTE: Install this hardware on the support Item 63 installed

previously.

24 On the right hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 19, between the Frame 39.1 and Frame

39.2 and between Stringers 48 and 46, install for Section W-W :

2 Spacer NSA5527-03-02 Item 141

2 Clamp NSA5516-07ND Item 179

or

2 Clamp NSA5516-08ND Item 180

or

2 Clamp NSA5516-10ND Item 181

and

2 Washer NAS1149F0332P Item 172

2 Screw NAS1801-3-17 Item 171

NOTE: Depends on aircraft configuration, use the PN NSA5516-07ND

or NSA5516-08ND or NSA5516-10ND for Item 170.

NOTE: Install this hardware on the support Item 64 installed

previously.

25 On the right hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 19, between the Frame 39.1 and Frame

39.2 and between Stringers 48 and 46, install for Section V-V :

1 Stud NSA5159-27 Item 163

1 Spacer NSA5527-03-01 Item 16

1 Clamp NSA935807-16 Item 134

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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1 Spacer NSA5527-03-08 Item 152

1 Clamp NSA935807-20 Item 135

1 Washer NSA935808-01 Item 153

1 Nut NSA5050-3 Item 154

NOTE: Install this hardware on the support Item 64 installed

previously.

26 On the right hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 20, between the Frame 39.1 and Frame

39.2 and between Stringers 47 and 46, remove for detail T :

1 Screw Item (136) Discard

1 Washer Item (153) Discard

1 Clamp Item (135) Retain

1 Clamp Item (134) Retain

27 On the right hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 20, between the Frame 39.1 and Frame

39.2 and between Stringers 47 and 46, install for detail U :

1 Stud NSA5159-17 Item 151

1 Spacer NSA5527-03-02 Item 141

1 Clamp Item (134) Retained at

removal

1 Spacer NSA5527-03-05 Item 165

1 Clamp Item (135) Retained at

removal

1 Washer NSA935808-01 Item 153

1 Nut NSA5050-3 Item 154

28 On the right hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 20, between the Frame 39.1 and Frame

39.2 and between Stringers 47 and 46, remove for detail Y :

1 Screw Item (143) Discard

1 Washer Item (133) Discard

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 152

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1 Clamp Item (155) Retain

1 Clamp Item (155) Retain

29 On the right hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 20, between the Frame 39.1 and Frame

39.2 and between Stringers 47 and 46, install for detail Z :

1 Stud NSA5159-27 Item 163

1 Clamp Item (155) Retained at

removal

1 Clamp Item (155) Retained at

removal

1 Spacer NSA5527-03-08 Item 152

1 Spacer NSA5527-03-15 Item 22

1 Clamp NSA935807-04 Item 150

1 Washer NSA935808-03 Item 131

1 Nut NSA5050-3 Item 154

30 On the right hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 20, between the Frame 39.1 and Frame

39.2 and between Stringers 46 and 45, remove for detail W :

1 Screw Item (136) Discard

1 Washer Item (153) Discard

1 Clamp Item (135) Retain

1 Clamp Item (134) Discard

31 On the right hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 20, between the Frame 39.1 and Frame

39.2 and between Stringers 46 and 45, install for detail X :

1 Stud NSA5159-10 Item 157

And

1 Clamp NSA5516-21ND Item 176

Or

1 Clamp NSA5516-22ND Item 177

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 153

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Or

1 Clamp NSA5516-23ND Item 178

And

1 Spacer NSA5527-03-01 Item 16

1 Spacer NSA5527-03-08 Item 152

1 Clamp Item (135) Retained at

removal

1 Washer NSA935808-01 Item 153

1 Nut NSA5050-3 Item 154

NOTE: Depends on aircraft configuration, use the PN NSA5516-21ND

or NSA5516-22ND or NSA5516-23ND for Item 166.

32 On the right hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 21, between the Frame 39.1 and Frame

39.2 and between Stringers 44 and 43, remove for detail AA :

1 Screw Item (136) Discard

1 Washer Item (153) Discard

1 Clamp Item (135) Retain

1 Clamp Item (134) Discard

33 On the right hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 21, between the Frame 39.1 and Frame

39.2 and between Stringers 44 and 43, install for detail AB :

1 Stud NSA5159-17 Item 151

And

1 Clamp NSA5516-21ND Item 176

Or

1 Clamp NSA5516-22ND Item 177

Or

1 Clamp NSA5516-23ND Item 178

And

1 Spacer NSA5527-03-11 Item 18

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 154

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1 Clamp Item (135) Retained at

removal

1 Washer NSA935808-01 Item 153

1 Nut NSA5050-3 Item 154

NOTE: Depends on aircraft configuration, use the PN NSA5516-21ND

or NSA5516-22ND or NSA5516-23ND for Item 166.

34 On the right hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 21, between the Frame 39.1 and Frame

39.2 and between Stringers 42 and 38, remove for detail AC :

3 Screw Item (136) Discard

3 Washer Item (153) Discard

3 Clamp Item (135) Retain

3 Clamp Item (134) Discard

35 On the right hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 21, between the Frame 39.1 and Frame

39.2 and between Stringers 42 and 38, install for detail AD :

3 Clamp NSA5516-21ND Item 176

Or

3 Clamp NSA5516-22ND Item 177

Or

3 Clamp NSA5516-23ND Item 178

And

3 Clamp Item (135) Retained at

removal

3 Washer NSA935808-01 Item 153

3 Screw NAS1801-3-10 Item 167

NOTE: Depends on aircraft configuration, use the PN NSA5516-21ND

or NSA5516-22ND or NSA5516-23ND for Item 166.

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 155

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SERVICE BULLETIN

36 On the right hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 21, along the Frame 39.1 and between

Stringers 38 and 37, remove for detail AE :

1 Screw Item (153) Discard

1 Washer Item (142) Discard

1 Clamp Item (135) Retain

37 On the right hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 21, between the Frame 39.1 and Frame

39.2 and between Stringers 38 and 37, install for detail AF :

1 Clamp Item (135) Retained at

removal

1 Washer NSA935808-01 Item 153

1 Screw NAS1801-3-9 Item 158

NOTE: Install this hardware on the support Item (88) installed

previously.

(b) Install the new route 2SG between FIN 302HF located on the left hand side at

stringer 36 and Frame 40 and the FIN 3520VC located in the avionics compartment

:

1 Remove the pressure seal 3520VP :

Refer to ESPM 20-43-42 and to Fig. A-FBMAA Sheet 22

a Remove :

2 Fitting-Seal NSA934710T11 Item (184) Discard

And

3 Spring NSA934710E20 Item (183) Discard

Attached with :

4 Screw NAS1801-3-12 Item (166) Discard

4 Washer ASNA2397-10L Item (14) Discard

4 Nut MS21042-3 Item (170) Discard

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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SERVICE BULLETIN

2 Put in position :

FIN 301HF

1 Cable-Electrical

Interconnecting

35301-74 Item 174

3 Install :

20 (M) Conduit E0432A04

4 Using supports installed at paragraph 3.C.(20).(a), route the wire No.

3622-0540 spliced at paragraph 3.C.(20).(b).2, from FIN 301HF located on the

left hand side at stringer 36 and at Frame 40, through pressure seal 3520VP,

to 3520VC located in avionics compartment as shown in Fig. A-FCCAA Sheet

01 and in Fig. A-FBMAA Sheet 01.

NOTE: The route 2SG rejoins route 2S on the right hand side at

stringer 46 between Frame 39.1 and Frame 39.2 as shown in

Fig. A-FBMAA Sheet 17.

5 Connect the wire No. 3622-0540 as shown on the wiring diagram, Fig. AFCCAA Sheet 01 and as given in the Hook-up Chart lines :

- 1 and 2 (Refer to Fig. A-FCCAA Sheet 02).

NOTE: Use the contacts supplied in :

Bundle F9000095227895

6 Install the splice FIN 3591VS (PN NSA936809RG0002) between the FIN

301HF and the wire No. 3622-0540 supplied in :

Bundle F9000095227895

NOTE: After connection, Secure the FIN 301HF and FIN 302HF with

Wire-lock MS20995C32 item 27.

7 Install the pressure seal 3520VP :

Refer to ESPM 20-43-42 and to Fig. A-FBMAA Sheet 22

a Install :

2 Fitting-Seal NSA934710T11 Item 184

And

3 Spring NSA934710E20 Item 183

Attach with :

4 Screw NAS1801-3-12 Item 166

4 Washer ASNA2397-10L Item 14

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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SERVICE BULLETIN

4 Nut MS21042-3 Item 170

8 Identify the splice FIN 3591VS with the identification sleeves and the

identification label supplied in :

Bundle F9000095227895

9 On the fuselage close to the plugs, identify the FIN 301HF with :

1 Placard F1131031522100

(23) Subtask 364033-831-201-001 - Install the electrical wiring in the FWD cargo

compartment

Work Zones and Access Panels

Zone Access/Work location

130 Work location from Frame 19 to Frame 37.1

Manpower Resources

Manhours 7.50

Minimum number of person 2

Subtask elapsed time 3.50

Skills ELECTRICAL

Material necessary to do the job

Kit 364033D01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

400 F9297000500000 1 EQUIPMNT

402 F9237000207400 2 PLCRDSET

404 NSA935401-03 100 TIE

405 NSA935401-04 100 TIE

406 NSA935401-05 100 TIE

407 NSA935401-10 100 TIE

References

Fig. A-GBAAA

Installation of the Electrical Wiring in the

FWD Cargo Compartment

Sheet 01

Fig. A-GHAAA

Hook-up Chart

Sheet 01

Fig. A-GHBAA

Hook-up Chart

Sheet 01

Fig. A-GWAAA

Wiring Diagram

Sheet 01

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 158

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SERVICE BULLETIN

(a) Install the electrical wiring in the FWD cargo compartment

1 Install the electrical wires:

Refer to Fig. A-GBAAA Sheet 01

Refer to Fig. A-GHAAA Sheet 01, Line 1 thru 2, END 1,

Refer to Fig. A-GWAAA Sheet 01

supplied with:

1 Equipment AssyElectricalF9297000500000 Item 400

2 Attach the electrical wires with:

Refer to Fig. A-GBAAA Sheet 01

100 Tie-Cable NSA935401-03 Item 404

100 Tie-Cable NSA935401-04 Item 405

100 Tie-Cable NSA935401-05 Item 406

100 Tie-Cable NSA935401-10 Item 407

Install the identification placards

2 Placard Set F9237000207400 Item 402

(24) Subtask 364033-831-202-001 - Install the electrical wiring in the AFT cargo

compartment and Bulk cargo compartment

Work Zones and Access Panels

Zone Access/Work location

From 150 Work location Frame 55

To 170 Work location Frame 80

Manpower Resources

Manhours 11.00

Minimum number of person 2

Subtask elapsed time 5.50

Skills ELECTRICAL

Material necessary to do the job

Kit 364033D01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

400 F9297000500000 1 EQUIPMNT

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 159

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SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

402 F9237000207400 4 PLCRDSET

404 NSA935401-03 100 TIE

405 NSA935401-04 100 TIE

406 NSA935401-05 100 TIE

407 NSA935401-10 100 TIE

References

Fig. A-GBBAA

Installation of the Electrical Wiring in the

AFT Cargo Compartment

Sheet 01

Sheet 02

Fig. A-GHAAA

Hook-up Chart

Sheet 01

Fig. A-GHBAA

Hook-up Chart

Sheet 01

Fig. A-GWAAA

Wiring Diagram

Sheet 01

(a) Install the electrical wiring in the AFT cargo compartment and Bulk cargo

compartment

1 Install the electrical wires on 5866VB between Frame 55 thru Frame 80/82:

Refer to Fig. A-GBBAA Sheet 01

Refer to Fig. A-GWAAA Sheet 01

Refer to Fig. A-GHAAA Sheet 01, Line 1 thru 3, END 1,

supplied with:

1 Equipment AssyElectricalF9297000500000 Item 400

2 Attach the electrical wires with:

Refer to Fig. A-GBBAA Sheet 01

100 Tie-Cable NSA935401-03 Item 404

100 Tie-Cable NSA935401-04 Item 405

100 Tie-Cable NSA935401-05 Item 406

100 Tie-Cable NSA935401-10 Item 407

Install the identification placards

4 Placard Set F9237000207400 Item 402

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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SERVICE BULLETIN

3 Route the electrical wires through the thermal insulator at Frame 80/82:

Refer to Fig. A-GBBAA Sheet 02

1 Insulator-Cable

Protection

ABS0596S006 Item (403)

(25) Subtask 364033-831-203-001 - Modify the electrical wiring in the AFT cargo

compartment, Bulk cargo compartment and Rear fuselage section

Manpower Resources

Manhours 4.50

Minimum number of person 1

Subtask elapsed time 4.50

Skills ELECTRICAL

References

Fig. A-GBCAA

Preparation for the Electrical Wiring

Installation in the Rear Fuselage Section

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

Sheet 09

Sheet 10

Fig. A-GHAAA

Hook-up Chart

Sheet 01

Fig. A-GHBAA

Hook-up Chart

Sheet 01

(a) Remove the pressure seal 5208VP from the pressure Frame at Frame 80/82

Refer to Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet 03

Remove:

1 Plate F9249011000200 Item (410) Retain

1 Plate F9249011000400 Item (411) Retain

2 Bulkhead Item (415) Discard

8 Screw Item (416) Discard

12 Washer Item (417) Discard

4 Washer Item (418) Discard

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 161

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SERVICE BULLETIN

4 Nut Item (419) Discard

or if alternate installed remove:

12 Washer Item (417) Discard

4 Washer Item (418) Discard

4 Nut Item (419) Discard

4 Screw Item (420) Discard

2 Screw Item (423) Discard

(b) Remove the lightning protection of the electrical bundle 5886VB at Frame 90

Refer to Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet 08

1 At Frame 90 loosen the electrical receptacle 5215VC, Item (435).

Refer to Fig. A-GBCAA Sheet 04 thru Fig. A-GBCAA Sheet 05

4 Screw Item (430) Discard

4 Washer Item (431) Discard

4 Nut Item (432) Discard

2 Disconnect the electrical wires end from the electrical receptacle 5215VC.

Refer to Fig. A-GBCAA Sheet 04 thru Fig. A-GBCAA Sheet 05

Refer to Fig. A-GHAAA Sheet 01 END 2, Line 4 thru 25 Fig. A-GHBAA Sheet

01 END 2, Line 1 and 2

Remove:

1 Receptacle Item (435) Retain

3 Remove from Frame 91

Refer to Fig. A-GBCAA Sheet 04 thru Fig. A-GBCAA Sheet 05

1 Screw Item (314) Discard

1 Washer Item (417) Discard

1 Clamp Item (437) Discard

1 Clip nut Item (353) Discard

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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4 Remove the lightning protection from the electrical bundle 5886VB at Frame

90

Refer to Fig. A-GBCAA Sheet 04 thru Fig. A-GBCAA Sheet 08

8 Screw Item (314) Discard

12 Washer Item (417) Discard

3 Nut Item (419) Discard

21 Clamp Item (437) Retain

3 Spacer Item (442) Retain

1 Clamp Item (443) Retain

4 Screw Item (444) Discard

1 Clip nut Item (448) Discard

or if alternate installed remove:

1 Washer Item (417) Discard

2 Spacer Item (442) Retain

3 Clamp Item (437) Retain

1 Clip nut Item (439) Discard

1 Screw Item (501) Discard

(c) Disconnect the electrical wiring 5865VB from the APU overhead leak detection

system at Frame 93

Refer to Fig. A-GBCAA Sheet 01, Fig. A-GBCAA Sheet 09 thru Fig. A-GBCAA

Sheet 10

Refer to Fig. A-GHAAA Sheet 01

1 Remove between Frame 92 thru Frame 93:

Refer to Fig. A-GBCAA Sheet 09 thru Fig. A-GBCAA Sheet 10

1 Washer Item (417) Discard

1 Nut Item (419) Discard

2 Clamp Item (437) Retain

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 163

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SERVICE BULLETIN

1 Screw Item (449) Discard

1 Spacer Item (464) Retain

1 Screw Item (465) Discard

1 Nut Item (470) Discard

1 Washer Item (471) Discard

2 Remove from Frame 93:

Refer to Fig. A-GBCAA Sheet 09

2 Washer Item (417) Discard

4 Spacer Item (442) Retain

2 Clamp Item (437) Retain

2 Clip nut Item (448) Discard

2 Screw Item (501) Discard

3 Remove the electrical splice 5151VSA from Frame 93:

Refer to Fig. A-GBCAA Sheet 09 thru Fig. A-GBCAA Sheet 10

Refer to Fig. A-GHAAA Sheet 01 END 2, Line 4 and 5

1 Sleeve Item (479) Discard

1 Sleeve Item (480) Discard

1 Splice Item (481) Discard

(26) Subtask 364033-831-205-001 - Install an additional profile in the Rear fuselage

section

Work Zones and Access Panels

Zone Access/Work location

310 Work location from Frame 90 to Frame 91

Stringer 6RH

Manpower Resources

Manhours 3.00

Minimum number of person 1

Subtask elapsed time 3.00

Skills AIRFRAME

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 164

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SERVICE BULLETIN

Material necessary to do the job

Kit 364033D03R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

314 NAS1801-3-8 2 SCREW

460 F5397083308600 1 SECTION

461 MS21047L3 1 NUT

462 EN6101AD3-08 2 RIVET

463 NAS1149D0332J 2 WASHER

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Corrosion Inhibitive interfay

Sealant

09-005

Corrosion Inhibiting, Fillet

Consistency

09-016 As required

Corrosion Inhibiting low

Adhesion Sealant

09-018

References

Fig. A-GBEAA

Installation of the Bracket between FR90

and FR91

Sheet 01

(a) Install an additional profile in the Rear fuselage section

1 Between Frame 90 thru Frame 91, at RH STGR6, temporarily put into position

Refer to Fig. A-GBEAA Sheet 01

1 Section Assy F5397083308600 Item 460

2 Transfer drill the holes and open holes to final dimension and install:

1 Nut MS21047L3 Item 461

with:

2 Rivet EN6101AD3-08 Item 462

NOTE: For dimensions refer to the table on Fig. A-GBEAA Sheet 01.

3 Between Frame 90 thru Frame 91, at RH STGR6, install:

1 Section Assy F5397083308600 Item 460

with:

2 Screw NAS1801-3-8 Item 314

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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2 Washer NAS1149D0332J Item 463

and protect the surface with:

Corrosion Inhibitive

interfay Sealant

09-005 As required

and

Corrosion Inhibiting,

Fillet Consistency

09-016 As required

, and seal the edges with:

Corrosion Inhibiting

low Adhesion

Sealant

09-018 As required

(27) Subtask 364033-831-204-001 - Install the electrical wiring in the rear fuselage

section

Work Zones and Access Panels

Zone Access/Work location

310 Work location from Frame 80/82 to Frame 93

Manpower Resources

Manhours 14.00

Minimum number of person 2

Subtask elapsed time 7.00

Skills ELECTRICAL

Material necessary to do the job

Kit 364033D01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

314 NAS1801-3-8 8 SCREW

320 NSA5527-03-02 5 SPACER

350 AS21919WCH13 6 CLAMP

351 MS21919WCH14 1 CLAMP

352 MS21919WCH8 1 CLAMP

353 NSA5067-3-1 1 NUT

400 F9297000500000 1 EQUIPMNT

402 F9237000207400 10 PLCRDSET

404 NSA935401-03 100 TIE

405 NSA935401-04 100 TIE

406 NSA935401-05 50 TIE

415 NSA934710T14 2 FITTING

416 NAS1801-3-9 8 SCREW

417 NAS1149C0332R 24 WASHER

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 166

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SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

418 NAS1149D0363K 4 WASHER

419 NAS1291C3M 10 NUT

420 NAS1102-3-10 4 SCREW

423 NAS1801-3-10 2 SCREW

430 NAS1100-04-6 4 SCREW

431 NAS1149CN416R 4 WASHER

432 MS21042-04 4 NUT

439 NSA5066-3-1 1 NUT

444 NAS1801-3-18 3 SCREW

448 NSA5066-3-2 1 NUT

449 NAS1801-08-8 2 SCREW

451 F9249016013200 1 PROTSYS

465 NAS1801-3-15 1 SCREW

469 ASNA0182-4ADL 2 STRIP

470 NAS1291C08M 3 NUT

471 NAS1149CN816R 5 WASHER

472 ASNA0182-3ADL 1 STRIP

475 NAS1801-08-36 2 SCREW

476 NSA5066-08-1 2 NUT

479 E0718-01 0.06 TUBING

480 NSA937210MB0300 0.1 TUBING

481 NSA936809RG0001 2 SPLICE

485 NSA934710E20 3 SPRING

488 E0126-06L 0.2 TUBING

489 F9249016510800 1 PROTSYS

492 ABS0580A17P 1 FITTING

493 NAS1801-3-21 2 SCREW

494 NSA935808C03 2 WASHER

496 NSA5527-03-08D 2 SPACER

501 NAS1801-3-27 2 SCREW

510 E0126-01L 0.35 TUBING

511 F9249016110900 1 PROTSYS

515 AS21919WCH07 1 CLAMP

517 ABS0513-09 1 SUPPORT

518 ABS0520-07P 1 NUT

521 AS21919WCH14 1 CLAMP

528 NAS1801-08-12 1 SCREW

536 AS21919WCH02 3 CLAMP

537 AS21919WCH09 1 CLAMP

843 MS21919WCH12 1 CLAMP

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 167

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References

Fig. A-GBDAA

Installation of the Electrical Wiring in the

Rear Fuselage Section

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

Sheet 09

Sheet 10

Sheet 11

(a) Install the electrical wire in the rear fuselage section

1 Install the electrical wire, Item 400, on 5866VB between Frame 80/82 thru

Frame 90

Refer to Fig. A-GBDAA Sheet 01

1 Equipment AssyElectricalF9297000500000 Item 400

Attach the wire with:

2 Placard Set F9237000207400 Item 402

100 Tie-Cable NSA935401-03 Item 404

100 Tie-Cable NSA935401-04 Item 405

50 Tie-Cable NSA935401-05 Item 406

2 Install the electrical wire on 5866VB with the pressure seal 5208VP at Frame

80/82

Refer to Fig. A-GBDAA Sheet 01 thru Fig. A-GBDAA Sheet 03

Install:

1 Plate F9249011000200 Item (410) Retained at

removal

1 Plate F9249011000400 Item (411) Retained at

removal

with:

2 Fitting-Seal NSA934710T14 Item 415

8 Screw NAS1801-3-9 Item 416

12 Washer NAS1149C0332R Item 417

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 168

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4 Washer NAS1149D0363K Item 418

4 Nut NAS1291C3M Item 419

4 Screw NAS1102-3-10 Item 420

2 Screw NAS1801-3-10 Item 423

NOTE: Alternative to two of the, Item 416.

3 Spring NSA934710E20 Item 485

3 Install the lightning protection of the electrical bundle 5886VB at Frame 90.

Attach to the wires on 5866VB leaving thru the 3 way transition at Frame 90

Refer to Fig. A-GBDAA Sheet 04

0.1 Tubing-Heat-Shrinkable E0126-06L Item 488

NOTE: Cut the sleeve to the necessary length.

4 Route the wires on 5866VB between Frame 90 thru Frame 91

Refer to Fig. A-GBDAA Sheet 04, Fig. A-GBDAA Sheet 08 thru Fig. A-GBDAA

Sheet 09

Install:

1 Protection SystemLightningF9249016510800 Item 489

with:

1 Washer NAS1149C0332R Item 417

1 Screw NAS1801-3-18 Item 444

1 Clamp AS21919WCH13 Item 350

1 Clamp Item (437) Retained at

removal

1 Spacer Item (442) Retained at

removal

5 Route the electrical wires:

Refer to Fig. A-GBDAA Sheet 04 and Fig. A-GBDAA Sheet 08

1 Fitting-Conduit ABS0580A17P Item 492

and install, Item 492, at Frame 90 with:

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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1 Clamp MS21919WCH14 Item 351

2 Nut NAS1291C3M Item 419

1 Strip ASNA0182-4ADL Item 469

2 Screw NAS1801-3-21 Item 493

2 Washer NSA935808C03 Item 494

2 Spacer NSA5527-03-08D Item 496

1 Clamp MS21919WCH12 Item 843

6 Route the electrical wires on 5866VB between Frame 90 thru Frame 91 to

connector 5215VC

Refer to Fig. A-GBDAA Sheet 04 thru Fig. A-GBDAA Sheet 08

Reinstall the connector 5215VC

1 Receptacle Item (435) Retained at

removal

attached with:

4 Screw NAS1100-04-6 Item 430

4 Washer NAS1149CN416R Item 431

4 Nut MS21042-04 Item 432

and install:

1 Screw NAS1801-3-8 Item 314

1 Washer NAS1149C0332R Item 417

2 Clamp Item (437) Retained at

removal

1 Nut-Clip NSA5066-3-2 Item 448

or alternative install:

1 Washer NAS1149C0332R Item 417

3 Clamp Item (437) Retained at

removal

1 Nut-Clip NSA5066-3-1 Item 439

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 170

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2 Spacer Item (442) Retained at

removal

1 Screw NAS1801-3-27 Item 501

and install:

12 Clamp Item (437) Retained at

removal

2 Spacer Item (442) Retained at

removal

5 Clamp AS21919WCH13 Item 350

8 Washer NAS1149C0332R Item 417

7 Screw NAS1801-3-8 Item 314

1 Screw NAS1801-3-27 Item 501

2 Spacer NSA5527-03-02 Item 320

3 Nut NAS1291C3M Item 419

2 Screw NAS1801-3-18 Item 444

1 Nut NSA5067-3-1 Item 353

7 Route the wire, Item 400, from the 3 way transition, Item 492, to the splice

5410VS and route to the wire 5866VB with:

Refer to Fig. A-GBDAA Sheet 04 and Fig. A-GBDAA Sheet 08

1 Protection SystemLightningF9249016013200 Item 451

1 Protection SystemLightningF9249016510800 Item 489

1 Protection SystemLightningF9249016110900 Item 511

0.1 Tubing-Heat-Shrinkable E0126-06L Item 488

0.35 Tubing-Heat-Shrinkable E0126-01L Item 510

NOTE: Cut the sleeve to the necessary length.

and install:

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 171

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SERVICE BULLETIN

8 Placard Set F9237000207400 Item 402

8 Install the protection, Item 511, at Frame 93 with:

1 Nut ABS0520-07P Item 518

1 Support-Strain Relief ABS0513-09 Item 517

9 Install the electrical wire at Frame 93on 5865VB and 5866VB with:

Refer to Fig. A-GBDAA Sheet 01 and Fig. A-GBDAA Sheet 10 thru Fig. AGBDAA Sheet 11

Install:

3 Spacer NSA5527-03-02 Item 320

1 Clamp MS21919WCH8 Item 352

1 Washer NAS1149C0332R Item 417

1 Nut NAS1291C3M Item 419

6 Clamp Item (437) Retained at

removal

5 Spacer Item (442) Retained at

removal

2 Screw NAS1801-08-8 Item 449

1 Screw NAS1801-3-15 Item 465

1 Strip ASNA0182-4ADL Item 469

3 Nut NAS1291C08M Item 470

5 Washer NAS1149CN816R Item 471

1 Strip-Bonding ASNA0182-3ADL Item 472

2 Screw NAS1801-08-36 Item 475

2 Nut-Clip NSA5066-08-1 Item 476

1 Clamp AS21919WCH07 Item 515

1 Clamp AS21919WCH14 Item 521

1 Screw NAS1801-08-12 Item 528

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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SERVICE BULLETIN

3 Clamp AS21919WCH02 Item 536

1 Clamp AS21919WCH09 Item 537

for the wire connection install:

0.06 Tubing-Heat-Shrinkable E0718-01 Item 479

0.1 Tubing-Heat Shrink NSA937210MB0300 Item 480

2 Splice NSA936809RG0001 Item 481

(28) Subtask 364033-831-206-001 - Remove the sensing elements in the AFT and Bulk

cargo compartments

Work Zones and Access Panels

Zone Access/Work location

From 160 Work location Frame 55

To 310 Work location Frame 83

Manpower Resources

Manhours 5.25

Minimum number of person 1

Subtask elapsed time 5.25

Skills ELECTRICAL

References

Fig. A-GBFAA

Removal of the Sensing Elements in the

Bulk and AFT Cargo Compartments

Sheet 01

Sheet 02

Sheet 03

(a) Remove the sensing elements from the APU bleed air duct in the AFT and Bulk

cargo compartments

1 Remove the sensing elements between Frame 55 thru Frame 83

Refer to Fig. A-GBFAA Sheet 01 thru Fig. A-GBFAA Sheet 03

Remove:

FIN 27HF

1 Sensing Element 35609-2-255 Item (562)

FIN 28HF

1 Sensing Element 35593-2-255 Item (564)

FIN 29HF

1 Sensing Element 35593-2-255 Item (566)

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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SERVICE BULLETIN

FIN 30HF

1 Sensing Element 35609-2-255 Item (563)

FIN 31HF

1 Sensing Element 35609-2-255 Item (570)

FIN 32HF

1 Sensing Element 35609-2-255 Item (572)

attached with:

6 Nut Item (612) Retain

5 Flange Item (592) Discard

15 Sleeve Item (602) Discard

15 Clamp Item (357) Discard

8 Screw Item (408) Retain

8 Spacer Item (609) Discard

16 Clip Nut Item (399) Retain

16 Screw Item (601) Retain

2 Remove the connector of the sensing element at Frame 80/82

Refer to Fig. A-GBFAA Sheet 01 and Fig. A-GBFAA Sheet 03

Remove:

1 Connector Item (355) Discard

3 Washer Item (596) Discard

(29) Subtask 364033-831-212-001 - Drill an additional hole for the dual loop overheat

leak detection in the sheet metal pressure bulkhead

Manpower Resources

Manhours 0.75

Minimum number of person 1

Subtask elapsed time 0.75

Skills AIRFRAME

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 174

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SERVICE BULLETIN

References

Fig. A-GBMAA

Hole Location and Dimensions for the

sensing element Installation in the Sheet

Metal Pressure Bulkhead

Sheet 01

(a) Drill the hole for the dual loop overheat leak detection in the pressure bulkhead

For dimensions refer to Fig. A-GBMAA Sheet 01

1 Drill the additional sensing element hole into the pressure bulkhead Frame

80/82 with a diameter of 13.5mm (0.53in.)

(30) Subtask 364033-831-207-001 - Install the sensing elements in the AFT and Bulk

cargo compartments

Work Zones and Access Panels

Zone Access/Work location

From 160 Work location Frame 55

To 310 Work location Frame 83

Manpower Resources

Manhours 11.25

Minimum number of person 1

Subtask elapsed time 11.25

Skills ELECTRICAL

Material necessary to do the job

Kit 364033D10R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

57 D3627006026600 1 PLACARD

355 NSA5549-00 1 CONNECTR

356 F3627011520400 1 PLACARD

357 NSA5543-00 22 CLAMP

562 35602-2-255 2 ELEMENT

563 35600-2-255 2 SNSGELEM

564 35586-2-255 2 ELEMENT

566 35594-2-255 2 SNSGELEM

570 35604-2-255 2 SNSGELEM

572 35597-2-255 1 SNSGELEM

574 35599-3-255 1 ELEMENT

591 F3627011520600 1 PLACARD

592 NSA5546-00 6 ANGLE

593 F3627011522200 1 PLACARD

594 F3627011520800 2 PLACARD

596 A2117050220000 1 RING

597 NAS1149C0832R 1 WASHER

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 175

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SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

602 NSA5539S 152 SLEEVE

604 NAS1149C0863R 1 WASHER

606 F3627011520200 2 PLACARD

607 NAS1919C04S02U 12 RIVET

609 NSA5527-03-01 1 SPACER

610 NSA5538-00 2 CLAMP

611 F3627011521000 1 PLACARD

612 NSA5542-00 6 NUT

805 NAS1802-3-13 1 SCREW

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Lockwire 0.6 Mm 19-018 As required

References

Aircraft Maintenance Manual (AMM) Task 36-22-17-400-801

Fig. A-GBGAA

Installation of the Sensing Elements in

the Bulk and AFT Cargo Compartments

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

Fig. A-GBNAA

Tolerances for the Waviness and Bend

in the Electrical Wiring

Sheet 01

Sheet 02

(a) Install the sensing elements in the AFT and Bulk cargo compartments

Refer to AMM Task 36-22-17-400-801

1 For the installation of the sensing elements install the connection flanges

Refer to Fig. A-GBGAA Sheet 01 thru Fig. A-GBGAA Sheet 08

Put the angles, Item 592, in position within the given tolerance area, transfer

drill the rivet holes to the duct-brackets with the diameter between 3.28 mm

and 3.35 mm (0.129 in and 0.132 in) and install:

6 Angle NSA5546-00 Item 592

with:

12 Rivet-Blind NAS1919C04S02U Item 607

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 176

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SERVICE BULLETIN

2 Install the sensing elements between Frame 55 thru Frame 83

Refer to Fig. A-GBGAA Sheet 01 thru Fig. A-GBGAA Sheet 08

For the tolerances for waviness and bend in wires, refer to Fig. A-GBNAA

Sheet 01 thru Fig. A-GBNAA Sheet 02.

NOTE: The length compensation of the sensing elements must be

done at the couplings or retainer rings.

NOTE: The sensing elements must be installed in front of the

ventilation holes.

Install:

2 Sensing Element 35602-2-255 Item 562

2 Sensing Element 35600-2-255 Item 563

2 Sensing Element 35586-2-255 Item 564

2 Sensing Element 35594-2-255 Item 566

2 Sensing Element 35604-2-255 Item 570

1 Sensing Element 35597-2-255 Item 572

1 Sensing Element 35599-3-255 Item 574

with:

1 Connector NSA5549-00 Item 355

22 Clamp NSA5543-00 Item 357

16 Clip Nut Item (399) Retained at

removal

6 Screw Item (408) Retained at

removal

1 Ring-Sealing A2117050220000 Item 596

1 Washer NAS1149C0832R Item 597

16 Screw Item (601) Retained at

removal

152 Sleeve-Protective NSA5539S Item 602

1 Washer NAS1149C0863R Item 604

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 177

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SERVICE BULLETIN

1 Spacer NSA5527-03-01 Item 609

2 Clamp NSA5538-00 Item 610

6 Nut NSA5542-00 Item 612

6 Nut Item (612) Retained at

removal

1 Screw NAS1802-3-13 Item 805

NOTE: Secure the nuts, Item 612/(612), with lockwire:

Lockwire 0.6 Mm 19-018 As required

3 Install the identification placards of the sensing-elements between Frame 55

thru Frame 83

Refer to Fig. A-GBGAA Sheet 01 thru Fig. A-GBGAA Sheet 07

Install:

1 Placard F3627011520400 Item 356

1 Placard F3627011520600 Item 591

2 Placard F3627011520800 Item 594

1 Placard F3627011522200 Item 593

1 Placard F3627011521000 Item 611

2 Placard F3627011520200 Item 606

1 Placard D3627006026600 Item 57

(31) Subtask 364033-410-003-001 - If removed, install the ducts between FR39 and

FR40.

Work Zones and Access Panels

Zone Access/Work location

190

Manpower Resources

Manhours 2.00

Minimum number of person 1

Subtask elapsed time 2.00

Skills AIRFRAME

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 178

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SERVICE BULLETIN

References

Fig. A-FBPAA

Removal/Installation of the Ducts

Between FR39 and FR40 for Access

Sheet 01

(a) Install :

Fig. A-FBPAA

(Refer to AMM Task 21-20-00-410-801)

1 Duct assy Item (125) Retained at

removal

1 Duct assy Item (126) Retained at

removal

1 Duct assy Item (127) Retained at

removal

(32) Subtask 364033-831-208-001 - Remove the sensing elements in the rear fuselage

Work Zones and Access Panels

Zone Access/Work location

310 Work location from Frame 80 to Frame 95

Manpower Resources

Manhours 2.75

Minimum number of person 1

Subtask elapsed time 2.75

Skills ELECTRICAL

References

Fig. A-GBHAA

Removal of the Sensing Elements in the

Rear Fuselage Section

Sheet 01

Sheet 02

Sheet 03

Sheet 04

(a) Remove the sensing elements in the rear fuselage

1 Remove the sensing elements between Frame 80/82 thru Frame 95

Refer to Fig. A-GBHAA Sheet 01 thru Fig. A-GBHAA Sheet 04

Remove:

FIN 33HF

1 Sensing Element 35660-2-310 Item (371) Discard

FIN 34HF

1 Sensing Element 35301-75 Item (361) Discard

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 179

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SERVICE BULLETIN

FIN 139HF

1 Sensing Element 35558-2-310 Item (364) Discard

FIN 140HF

1 Sensing Element 35636-2-310 Item (366) Discard

attached with:

3 Screw Item (601) Discard

35 Screw Item (601) Retain

39 Sleeve Item (602) Discard

6 Screw Item (620) Retain

6 Spacer Item (609) Retain

38 Clamp Item (610) Discard

37 Nut-Clip Item (399) Retain

1 Nut-Clip Item (399) Discard

3 Flange Item (59) Discard

3 Nut Item (612) Retain

2 Clamp Item (621) Retain

2 Remove the connector of the sensing element at Frame 80/82

Refer to Fig. A-GBHAA Sheet 01 thru Fig. A-GBHAA Sheet 04

Remove:

1 Connector Item (355) Discard

1 Washer Item (596) Discard

1 Washer Item (604) Discard

(33) Subtask 364033-831-209-001 - Install the sensing elements in the rear fuselage

Manpower Resources

Manhours 5.75

Minimum number of person 1

Subtask elapsed time 5.75

Skills ELECTRICAL

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 180

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SERVICE BULLETIN

Material necessary to do the job

Kit 364033D13R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

59 NSA5545-00 3 ANGLE

313 NAS1801-3-19 2 SCREW

355 NSA5549-00 1 CONNECTR

357 NSA5543-00 40 CLAMP

360 35301-74 1 CABLE

361 35301-75 1 CABLE

364 35566-2-310 2 ELEMENT

366 35624-2-310 2 ELEMENT

371 35661-2-310 1 ELEMENT

372 AS21919WCH04 12 CLAMP

373 AS21919WCH10 2 CLAMP

374 F3617052620200 1 PLACARD

392 F3627011521400 1 PLACARD

393 F3627011521600 2 PLACARD

394 F3627011521800 2 PLACARD

398 35659-3-310 1 ELEMENT

405 NSA935401-04 2 TIE

416 NAS1801-3-9 5 SCREW

496 NSA5527-03-08D 2 SPACER

591 F3617052620000 1 PLACARD

596 A2117050220000 1 RING

597 NAS1149C0832R 1 WASHER

602 NSA5539S 104 SLEEVE

604 NAS1149C0863R 1 WASHER

607 NAS1919C04S02U 6 RIVET

608 D3627006026800 1 PLACARD

609 NSA5527-03-01 4 SPACER

610 NSA5538-00 4 CLAMP

612 NSA5542-00 3 NUT

640 MS21042-3 5 NUT

682 NAS1149D0332K 7 WASHER

805 NAS1802-3-13 2 SCREW

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Lockwire 0.6 Mm 19-018 As required

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 181

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@A340

SERVICE BULLETIN

References

Fig. A-GBJAA

Installation of the Sensing Elements in

the Rear Fuselage Section

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

(a) Install the sensing elements in the rear fuselage

1 For the installation of the sensing elements install the connection flanges

Refer to Fig. A-GBJAA Sheet 01 thru Fig. A-GBJAA Sheet 08

Install:

3 Connection Flanges NSA5545-00 Item 59

with:

6 Rivet-Blind NAS1919C04S02U Item 607

2 Install the sensing elements between Frame 80/82 thru Frame 95

Refer to Fig. A-GBJAA Sheet 01 thru Fig. A-GBJAA Sheet 08

NOTE: The length compensation of the sensing elements must be

done at the couplings or retainer rings.

NOTE: The sensing elements must be installed in front of the

ventilation holes.

Install:

FIN 359HF

1 Sensing Element 35566-2-310 Item 364

FIN 139HF

1 Sensing Element 35566-2-310 Item 364

FIN 361HF

1 Cable-Electrical

Interconnecting

35301-74 Item 360

FIN 34HF

1 Cable-Electrical

Interconnecting

35301-75 Item 361

FIN 360HF

1 Sensing Element 35624-2-310 Item 366

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 182

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SERVICE BULLETIN

FIN 140HF

1 Sensing Element 35624-2-310 Item 366

FIN 358HF

1 Sensing Element 35659-3-310 Item 398

FIN 33HF

1 Sensing Element 35661-2-310 Item 371

with:

1 Connector NSA5549-00 Item 355

1 Washer NAS1149C0832R Item 597

1 Ring-Sealing A2117050220000 Item 596

1 Washer NAS1149C0863R Item 604

attached with:

37 Nut-Clip Item (399) Retained at

removal

35 Screw Item (601) Retained at

removal

6 Spacer Item (609) Retained at

removal

3 Nut Item (612) Retained at

removal

6 Screw Item (620) Retained at

removal

2 Clamp Item (621) Retained at

removal

2 Screw NAS1801-3-19 Item 313

40 Clamp NSA5543-00 Item 357

12 Clamp AS21919WCH04 Item 372

2 Clamp AS21919WCH10 Item 373

5 Screw NAS1801-3-9 Item 416

2 Spacer NSA5527-03-08D Item 496

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 183

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SERVICE BULLETIN

104 Sleeve-Protective NSA5539S Item 602

4 Spacer NSA5527-03-01 Item 609

4 Clamp NSA5538-00 Item 610

3 Nut NSA5542-00 Item 612

5 Nut MS21042-3 Item 640

7 Washer NAS1149D0332K Item 682

2 Screw NAS1802-3-13 Item 805

NOTE: Secure the nuts, Item 612/(612), with lockwire:

Lockwire 0.6 Mm 19-018 As required

3 Install the identification placards of the sensing-elements between Frame

80/82 thru Frame 95

Refer to Fig. A-GBJAA Sheet 01 thru Fig. A-GBJAA Sheet 08

Install:

1 Placard F3617052620200 Item 374

1 Placard F3627011521400 Item 392

2 Placard F3627011521600 Item 393

2 Placard F3627011521800 Item 394

2 Tie-Cable NSA935401-04 Item 405

1 Placard F3617052620000 Item 591

1 Placard D3627006026800 Item 608

(34) Subtask 364033-831-210-001 - Install the sleeves at the APU Bleed Air Duct

Work Zones and Access Panels

Zone Access/Work location

310 Work location from Frame 80 to Frame 95

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills ELECTRICAL

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 184

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SERVICE BULLETIN

Material necessary to do the job

Kit 364033D16R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

375 F3617062400000 1 SLEEVE

376 F3617062400200 1 SLEEVE

377 F3617062400400 1 SLEEVE

378 F3617062400600 1 SLEEVE

379 F3617062400800 1 SLEEVE

380 F3617062401000 1 SLEEVE

381 F3617062401200 1 SLEEVE

382 F3617062401400 1 SLEEVE

384 F3617062401800 1 SLEEVE

References

Fig. A-GBKAA

Installation of the Sleeves at the APU

Bleed Air Duct

Sheet 01

(a) Install the sleeves at the APU Bleed Air Duct between Frame 80/82 thru Frame 95

Refer to Fig. A-GBKAA Sheet 01

install the sleeves:

1 Sleeve Assy F3617062400000 Item 375

1 Sleeve Assy F3617062400200 Item 376

1 Sleeve Assy F3617062400400 Item 377

1 Sleeve Assy F3617062400600 Item 378

1 Sleeve Assy F3617062400800 Item 379

1 Sleeve Assy F3617062401000 Item 380

1 Sleeve Assy F3617062401200 Item 381

1 Sleeve Assy F3617062401400 Item 382

1 Sleeve Assy F3617062401800 Item 384

NOTE: Make sure that the blowout apertures of the blankets are close to

(under) the sensing elements.

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 185

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SERVICE BULLETIN

**CONF 002

(1) Subtask 364033-831-016-001 - Modify the Wiring between the Avionics

Compartment and the Cargo Compartment.

Work Zones and Access Panels

Zone Access/Work location

190

Manpower Resources

Manhours 2.00

Minimum number of person 2

Subtask elapsed time 2.00

Skills ELECTRICAL

Material necessary to do the job

Kit 364033A02R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

169 NSA935401-03 300 TIE

F9000095227895 BUNDLE

NSA935401-08 300 TIE

NSA935401-13 300 TIE

References

Fig. A-FBMAA

Installation of the New Harness 2SG

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

Sheet 09

Sheet 10

Sheet 11

Sheet 12

Sheet 13

Sheet 14

Sheet 15

Sheet 16

Sheet 17

Sheet 18

Sheet 19

Sheet 20

Sheet 21

Sheet 22

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 186

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SERVICE BULLETIN

References

Fig. A-FCBAA

Modification of the Wiring between the

Cargo Compartment and the Avionics

Compartment

Sheet 01

Sheet 02

(a) As shown in Fig. A-FBMAA Sheet 01, install the wire, using spares conduits

between Frame 37 and Frame 53.2, as shown on the wiring diagram, Fig. AFCBAA Sheet 01 and as given in the Hook-up Chart line :

- 1 (Refer to Fig. A-FCBAA Sheet 02) supplied in :

Bundle F9000095227895

NOTE: The spares conduits is divided in two parts. The first parts go away

from Frame 40 to Frame 47 and the second parts go away from

Frame 48 to Frame 53.2

(b) Attach the wires with :

300 Tie-Cable NSA935401-03 Item 169

300 Tie-Cable NSA935401-08

300 Tie-Cable NSA935401-13

(2) Subtask 364033-831-017-001 - Modify the Wiring in the Main rack 800VU.

Work Zones and Access Panels

Zone Access/Work location

120 Work location Electrical panel 800VU

Manpower Resources

Manhours 4.00

Minimum number of person 2

Subtask elapsed time 2.00

Skills ELECTRICAL

Material necessary to do the job

Kit 364033A02R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

169 NSA935401-03 50 TIE

F9000095227895 BUNDLE

NSA935401-06 50 TIE

NSA935401-13 50 TIE

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 187

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SERVICE BULLETIN

References

Aircraft Maintenance Manual (AMM) Task 36-11-34-000-802

Task 36-11-34-400-802

Fig. A-FCAAA

Modification of the Wiring in the Main

Rack 800VU

Sheet 01

Sheet 02

Sheet 03

Sheet 04

(a) Remove and retain the BMC (FIN 1HA1, 1HA2, 1HA3 and 1HA4) (Refer to AMM

Task 36-11-34-000-802).

(b) Remove the wires as shown on the wiring diagram Fig. A-FCAAA Sheet 01, and as

given in the Hook-up Chart lines :

- 1 thru 5 (Refer to Fig. A-FCAAA Sheet 04).

(c) Install the wires as shown on the wiring diagrams, Fig. A-FCAAA Sheet 02 and Fig.

A-FCAAA Sheet 03 and as given in the Hook-up Chart lines :

- 9 thru 19 (Refer to Fig. A-FCAAA Sheet 04) supplied in :

Bundle F9000095227895

(d) Attach the wires with :

50 Tie-Cable NSA935401-03 Item 169

50 Tie-Cable NSA935401-06

50 Tie-Cable NSA935401-13

(e) Install the BMC (FIN 1HA1, 1HA2, 1HA3 and 1HA4) (Refer to AMM Task

36-11-34-400-802).

(3) Subtask 364033-831-001-001 - Remove the sensing elements and the supports

between FR39 and FR44.

Work Zones and Access Panels

Zone Access/Work location

190 Work location from Frame 39 to Frame 44

Manpower Resources

Manhours 4.00

Minimum number of person 1

Subtask elapsed time 4.00

Skills AIRFRAME

References

Aircraft Maintenance Manual (AMM) Task 36-22-17-000-801

Task 36-22-17-000-802

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 188

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SERVICE BULLETIN

References

Fig. A-FBAAA

Removal of the Sensing Elements

between FR39 and FR55 on the LH side

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

(a) Remove :

Fig. A-FBAAA Sheet 01 Fig. A-FBAAA Sheet 02

(Refer to AMM Task 36-22-17-000-801 and AMM Task 36-22-17-000-802)

22 Screw Item (20) Discard

32 Washer Item (14) Discard

32 Clamp Item (86) Discard

32 Sleeve Item (13) Discard

5 Screw Item (91) Discard

10 Spacer Item (16) Discard

5 Screw Item (21) Discard

2 Nut Item (15) Discard

FIN 97HF

1 Sensing Element 35610-2-255 Item (1) Discard

FIN 98HF

1 Sensing Element 35624-2-255 Item (2) Discard

4 Rivet Item (11) Discard

2 Support Item (10) Discard

(4) Subtask 364033-831-002-001 - Remove the sensing elements and the supports

between FR44 and FR51.

Work Zones and Access Panels

Zone Access/Work location

190 Work location from Frame 44 to Frame 51

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 189

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SERVICE BULLETIN

Manpower Resources

Manhours 4.00

Minimum number of person 1

Subtask elapsed time 4.00

Skills AIRFRAME

References

Aircraft Maintenance Manual (AMM) Task 36-22-17-000-801

Fig. A-FBAAA

Removal of the Sensing Elements

between FR39 and FR55 on the LH side

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

(a) Remove :

Fig. A-FBAAA Sheet 01 Fig. A-FBAAA Sheet 03

(Refer to AMM Task 36-22-17-000-801)

18 Screw Item (21) Discard

30 Washer Item (14) Discard

30 Clamp Item (86) Discard

30 Sleeve Item (13) Discard

18 Spacer Item (16) Discard

12 Screw Item (20) Discard

2 Nut Item (15) Discard

FIN 99HF

1 Sensing Element 35612-2-255 Item (3) Discard

FIN 100HF

1 Sensing Element 35605-2-255 Item (6) Discard

4 Rivet Item (11) Discard

2 Support Item (10) Discard

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 190

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SERVICE BULLETIN

(5) Subtask 364033-831-003-001 - Remove the sensing elements and the supports

between FR51 and FR53.6.

Work Zones and Access Panels

Zone Access/Work location

190 Work location from Frame 51 to Frame 53.6

Manpower Resources

Manhours 4.00

Minimum number of person 1

Subtask elapsed time 4.00

Skills AIRFRAME

References

Aircraft Maintenance Manual (AMM) Task 36-22-17-000-801

Task 36-22-17-000-802

Fig. A-FBAAA

Removal of the Sensing Elements

between FR39 and FR55 on the LH side

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

(a) Remove :

Fig. A-FBAAA Sheet 01 Fig. A-FBAAA Sheet 04

(Refer to AMM Task 36-22-17-000-801 and AMM Task 36-22-17-000-802)

18 Screw Item (21) Discard

37 Washer Item (14) Discard

37 Clamp Item (86) Discard

37 Sleeve Item (13) Discard

23 Spacer Item (16) Discard

16 Screw Item (20) Discard

1 Screw Item (93) Discard

1 Spacer Item (18) Discard

2 Screw Item (91) Discard

3 Nut Item (15) Discard

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 191

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SERVICE BULLETIN

FIN 101HF

1 Sensing Element 35603-2-255 Item (4) Discard

FIN 102HF

1 Sensing Element 35600-2-255 Item (5) Discard

FIN 23HF

1 Sensing Element 35571-2-255 Item (7) Discard

6 Rivet Item (11) Discard

3 Support Item (10) Discard

(6) Subtask 364033-831-004-001 - Remove the sensing elements and the supports

between FR53.6 and FR55.

Work Zones and Access Panels

Zone Access/Work location

190 Work location from Frame 53.6 to Frame 55

Manpower Resources

Manhours 4.00

Minimum number of person 1

Subtask elapsed time 4.00

Skills AIRFRAME

References

Aircraft Maintenance Manual (AMM) Task 36-22-17-000-801

Fig. A-FBAAA

Removal of the Sensing Elements

between FR39 and FR55 on the LH side

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

(a) Remove :

Fig. A-FBAAA Sheet 01 Fig. A-FBAAA Sheet 05

(Refer to AMM Task 36-22-17-000-801)

19 Screw Item (20) Discard

27 Washer Item (14) Discard

27 Clamp Item (86) Discard

27 Sleeve Item (13) Discard

4 Screw Item (91) Discard

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 192

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SERVICE BULLETIN

12 Spacer Item (16) Discard

4 Screw Item (21) Discard

2 Nut Item (15) Discard

FIN 24HF

1 Sensing Element 35580-2-255 Item (8) Discard

FIN 25HF

1 Sensing Element 35611-3-255 Item (9) Discard

2 Rivet Item (11) Discard

1 Support Item (10) Discard

(7) Subtask 364033-010-002-001 - If necessary, remove the ducts between FR53.5 and

FR53.6 for access.

Work Zones and Access Panels

Zone Access/Work location

150 Work location from Frame 53.5 to Frame 53.6

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills AIRFRAME

References

Aircraft Maintenance Manual (AMM) Task 36-12-41-000-801

Fig. A-FBBAA

Removal/Installation of the Ducts

between FR53.6 and FR53.7 on the LH

side (for Access)

Sheet 01

(a) Remove :

Fig. A-FBBAA

(Refer to AMM Task 36-12-41-000-801)

1 Duct assy Item (112) Retain

1 Duct assy Item (112) Retain

1 Duct assy Item (114) Retain

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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SERVICE BULLETIN

(8) Subtask 364033-831-005-001 - Drill a new hole in the structure between FR53.5 and

FR53.6.

Work Zones and Access Panels

Zone Access/Work location

150 Work location from Frame 53.5 to Frame 53.6

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills AIRFRAME

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Chemical Conversion

Coating Yellow Aluminum

13-002 As required

Anti-Corrosion Primer

(polyurethane)

16-001 As required

Polyurethane Finnish Paint 16-018 As required

References

Fig. A-FBCAA

Drilling of a New Hole in the Structure

between FR53.5 and FR53.6 on the LH

side and Installation of Sensing

Elements

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

(a) Drill one hole on the structure between FR53.5 and FR53.6 to a diameter

comprised between 13.5mm (0.531in.) Min. and 13.7mm (0.539 in.) Max. as shown

on Fig. A-FBCAA.

(b) Do a spotfacing on the structure between FR53.5 and 53.6 to a diameter of 24mm

(0.944 in.) with a radius of 2mm (0.078in.)

NOTE: Be careful at the depth : 2mm (0.078 in.) Min. and 3mm (0.118 in.)

Max.

(c) Protect the hole and the spotfacing with :

Chemical

Conversion Coating

Yellow Aluminum

13-002 As required

Anti-Corrosion

Primer

(polyurethane)

16-001 As required

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 194

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SERVICE BULLETIN

Polyurethane

Finnish Paint

16-018 As required

(9) Subtask 364033-831-006-001 - Install a new support for the routing of the sensing

elements between FR53.5 and FR53.6.

Work Zones and Access Panels

Zone Access/Work location

150 Work location from Frame 53.5 to Frame 53.6

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills NON SPECIFIC

Material necessary to do the job

Kit 364033A01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

96 F5392059300000 1 SUPPORT

97 ASNA2050DCJ3215 2 RIVET

Reidentified part set REIDA01

ITEM NEW PART N ̊ KEYWORD ITEM OLD PART N ̊ SEE

NOTES

F0041196200000 BLANKET F2581571700000

F2582261900000

F0041196300000 BLANKET F2581566600000

F0041196400000 BLANKET F2581666600000

F0041196500000 BLANKET F2581677800000

F0041196600000 BLANKET F2581677900000

F0041196700000 BLANKET F2582242300000

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Adhesive Tape (insulation

Blanket Repair)

08-073 As required

Interfay Sealant 09-005A As required

Corrosion Inhibiting Fillet

Consistency

09-016B As required

References

Fig. A-FBFAA

Installation of a New Bracket between

FR53.5 and FR53.6

Sheet 01

Sheet 02

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 195

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(a) Move the insulation blanket to get access to the modification area.

(b) Put the bracket Item 96 in position as shown on Fig. A-FBFAA.

(c) Drill two holes on the structure to a diameter comprised between 3.25mm (0.128in.)

and 3.35mm (0.132in.) to match the holes of the bracket Item 96.

Fig. A-FBFAA

(d) Cut the insulation blanket to permit the installation of the bracket Item 96.

NOTE: For the repair of the insulation blanket use :

Adhesive Tape

(insulation Blanket

Repair)

08-073 As required

(e) Re-identify the insulation blanket :

1 Blanket-Insulation F2581571700000

or

1 Blanket-Insulation F2582261900000

becomes

1 Blanket-Insulation F0041196200000

or

1 Blanket-Insulation F2581566600000

becomes

1 Blanket-Insulation F0041196300000

or

1 Blanket-Insulation F2581666600000

becomes

1 Blanket-Insulation F0041196400000

or

1 Blanket-Insulation F2581677800000

becomes

1 Blanket-Insulation F0041196500000

or

1 Blanket-Insulation F2581677900000

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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SERVICE BULLETIN

becomes

1 Blanket-Insulation F0041196600000

or

1 Blanket-Insulation F2582242300000

becomes

1 Blanket-Insulation F0041196700000

(f) Install :

Fig. A-FBFAA

1 Support F5392059300000 Item 96

2 Rivet ASNA2050DCJ3215 Item 97

NOTE: To the interface of the new bracket and the structure, apply :

Interfay Sealant 09-005A As required

NOTE: Do a sealant bead around new parts with :

Corrosion Inhibiting

Fillet Consistency

09-016B As required

NOTE: Wet install the fasteners with :

Interfay Sealant 09-005A As required

(g) Install the insulation blanket.

(10) Subtask 364033-410-001-001 - If removed, install the ducts between FR53.5 and

FR53.6.

Work Zones and Access Panels

Zone Access/Work location

150 Work location from Frame 53.5 to Frame 53.6

Manpower Resources

Manhours 2.00

Minimum number of person 1

Subtask elapsed time 2.00

Skills AIRFRAME

References

Aircraft Maintenance Manual (AMM) Task 36-12-41-400-801

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 197

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References

Fig. A-FBBAA

Removal/Installation of the Ducts

between FR53.6 and FR53.7 on the LH

side (for Access)

Sheet 01

(a) Install :

(Refer to AMM Task 36-12-41-400-801)

1 Duct assy Item (112) Retained at

removal

1 Duct assy Item (112) Retained at

removal

1 Duct assy Item (114) Retained at

removal

(11) Subtask 364033-010-003-001 - If necessary, remove the ducts between FR43 and

FR45 for access.

Work Zones and Access Panels

Zone Access/Work location

190 Work location from Frame 43 to Frame 45

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 36-12-41-000-801

Fig. A-FBDAA

Removal/Installation of the Ducts

between FR44 and FR47 on the LH side

(for Access)

Sheet 01

(a) Remove :

(Refer to AMM Task 36-12-41-000-801)

1 Duct assy Item (115) Retain

1 Duct assy Item (116) Retain

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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SERVICE BULLETIN

(12) Subtask 364033-831-007-001 - Replace the web assy and the half clamp assy at

FR44.

Work Zones and Access Panels

Zone Access/Work location

190 Work location Frame 44

Manpower Resources

Manhours 3.00

Minimum number of person 1

Subtask elapsed time 3.00

Skills AIRFRAME

Material necessary to do the job

Kit 364033A01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

117 F5331591000200 1 WEB

118 F5331583500200 1 CLAMP

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Corrosion Inhibiting Fillet

Consistency

09-016B As required

Low Adhesion Polysulfide

Sealant

09-019B As required

References

Fig. A-FBEAA

Replacement of the Web Assy at FR44

on the LH side

Sheet 01

Sheet 02

(a) Remove :

Fig. A-FBEAA

17 Screw Item (119) Retain

17 Washer Item (124) Retain

1 Strip cover assy Item (122) Retain

2 Screw Item (120) Retain

1 Half clamp assy F5331583500000 Item (118) Discard

1 Half clamp assy Item (121) Retain

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 199

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1 Bracket Item (123) Retain

1 Web Assy F5331591000000 Item (117) Discard

NOTE: It is not necessary to remove completely the bracket Item (123).

(b) Install :

Fig. A-FBEAA

1 Web Assy F5331591000200 Item 117

1 Bracket Item (123) Retained at

removal

1 Half clamp assy Item (121) Retained at

removal

1 Half clamp assy F5331583500200 Item 118

2 Screw Item (120) Retained at

removal

1 Strip cover assy Item (122) Retained at

removal

17 Washer Item (124) Retained at

removal

17 Screw Item (119) Retained at

removal

NOTE: Install the new web assy with :

Corrosion Inhibiting

Fillet Consistency

09-016B As required

and

Low Adhesion

Polysulfide Sealant

09-019B As required

(13) Subtask 364033-831-008-001 - Install the new brackets for the routing of the

sensing elements at FR44.

Work Zones and Access Panels

Zone Access/Work location

190 Work location Frame 44

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 200

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Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills AIRFRAME

Material necessary to do the job

Kit 364033A01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

97 ASNA2050DCJ3215 2 RIVET

98 F0041178800000 1 SUPPORT

99 F0041178800100 1 SUPPORT

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Interfay Sealant 09-005A As required

Corrosion Inhibiting Fillet

Consistency

09-016B As required

References

Fig. A-FBGAA

Installation of Two New Brackets at

FR44

Sheet 01

Sheet 02

(a) Put the brackets Item 98 and 99 in position as shown on Fig. A-FBGAA.

(b) Drill two holes to a diameter comprised between 3.25mm (0.128in.) and 3.35mm

(0.132in.) as shown on Fig. A-FBGAA.

(c) Install :

1 Support F0041178800000 Item 98

1 Support F0041178800100 Item 99

2 Rivet ASNA2050DCJ3215 Item 97

NOTE: To the interface of the new bracket and the structure apply :

Interfay Sealant 09-005A As required

NOTE: Do a sealant bead around new parts with :

Corrosion Inhibiting

Fillet Consistency

09-016B As required

NOTE: Wet install the fasteners with :

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 201

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SERVICE BULLETIN

Interfay Sealant 09-005A As required

(14) Subtask 364033-410-002-001 - If removed, install the ducts between FR43 and

FR45.

Work Zones and Access Panels

Zone Access/Work location

190 Work location from Frame 43 to Frame 45

Manpower Resources

Manhours 2.00

Minimum number of person 1

Subtask elapsed time 2.00

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 36-12-41-400-801

Fig. A-FBDAA

Removal/Installation of the Ducts

between FR44 and FR47 on the LH side

(for Access)

Sheet 01

(a) Install :

(Refer to AMM Task 36-12-41-400-801)

1 Duct assy Item (115) Retained at

removal

1 Duct assy Item (116) Retained at

removal

(15) Subtask 364033-831-009-001 - Install the sensing elements and the supports

between FR39 and FR44.

Work Zones and Access Panels

Zone Access/Work location

190 Work location from Frame 39 to Frame 44

Manpower Resources

Manhours 14.00

Minimum number of person 1

Subtask elapsed time 14.00

Skills AIRFRAME

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 202

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SERVICE BULLETIN

Material necessary to do the job

Kit 364033A01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

10 NSA5543-00 30 CLAMP

11 ASNA0342T04-01 4 BOLT

13 NSA5539S 62 SLEEVE

14 ASNA2397-10L 34 WASHER

15 NSA5542-00 4 NUT

16 NSA5527-03-01 8 SPACER

18 NSA5527-03-11 6 SPACER

20 NAS6603-1 19 BOLT

21 NAS6603-9 8 BOLT

24 NAS6603-15 6 BOLT

29 NAS6603-2 2 BOLT

30 NSA5546-00 2 ANGLE

32 F1131031621700 2 PLACARD

33 F1131031623700 2 PLACARD

34 F1131031621800 1 PLACARD

35 F1131031623800 1 PLACARD

70 F3611548300000 1 SUPPORT

71 F3611548800000 1 SUPPORT

78 F3611549700000 1 SUPPORT

79 F3611549100000 1 SUPPORT

100 35606-2-255 1 SNSGELEM

101 35621-2-255 1 SNSGELEM

102 35620-2-255 1 SNSGELEM

113 35610-2-255 1 SNSGELEM

References

Fig. A-FBHAA

Installation of the New Sensing

Elements between FR39 and FR44 on

LH side

Sheet 01

Sheet 02

Sheet 03

Sheet 04

(a) Install the sensing elements and the supports between FR39 and FR40.2.

1 Install the supports between FR39 and FR40 :

1 Angle NSA5546-00 Item 30

2 Rivet-Blind ASNA0342T04-01 Item 11

8 Clamp NSA5543-00 Item 10

6 Spacer NSA5527-03-01 Item 16

2 Spacer NSA5527-03-11 Item 18

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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8 Washer ASNA2397-10L Item 14

6 Bolt NAS6603-9 Item 21

2 Bolt NAS6603-15 Item 24

2 Install the supports between FR40 and FR40.2 :

1 Support F3611549100000 Item 79

1 Support F3611549700000 Item 78

5 Clamp NSA5543-00 Item 10

1 Spacer NSA5527-03-01 Item 16

8 Washer ASNA2397-10L Item 14

1 Bolt NAS6603-9 Item 21

6 Bolt NAS6603-1 Item 20

2 Bolt NAS6603-2 Item 29

1 Angle NSA5546-00 Item 30

2 Rivet-Blind ASNA0342T04-01 Item 11

3 Install the placards between FR39 and FR40.2 :

2 Placard F1131031621700 Item 32

2 Placard F1131031623700 Item 33

1 Placard F1131031621800 Item 34

1 Placard F1131031623800 Item 35

4 Install the sensing elements between FR39 and FR40.2 :

FIN 97HF

1 Sensing Element 35606-2-255 Item 100

FIN 302HF

1 Sensing Element 35610-2-255 Item 113

28 Sleeve-Protective NSA5539S Item 13

4 Nut NSA5542-00 Item 15

NOTE: Secure the nuts Item 15 with wire-lock MS20995C32 Item 27.

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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(b) Install the sensing elements and the supports between FR40.2 and FR44.

1 Install the supports between FR40.2 and FR44 :

1 Support F3611548300000 Item 70

1 Support F3611548800000 Item 71

17 Clamp NSA5543-00 Item 10

4 Spacer NSA5527-03-11 Item 18

1 Spacer NSA5527-03-01 Item 16

18 Washer ASNA2397-10L Item 14

13 Bolt NAS6603-1 Item 20

1 Bolt NAS6603-9 Item 21

4 Bolt NAS6603-15 Item 24

2 Install the sensing elements between FR40.2 and FR44 :

FIN 98HF

1 Sensing Element 35620-2-255 Item 102

FIN 303HF

1 Sensing Element 35621-2-255 Item 101

34 Sleeve-Protective NSA5539S Item 13

(16) Subtask 364033-831-010-001 - Install the sensing elements and the supports

between FR44 and FR50.

Work Zones and Access Panels

Zone Access/Work location

190 Work location from Frame 44 to Frame 50

Manpower Resources

Manhours 14.00

Minimum number of person 1

Subtask elapsed time 14.00

Skills AIRFRAME

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 205

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Material necessary to do the job

Kit 364033A01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

10 NSA5543-00 29 CLAMP

11 ASNA0342T04-01 4 BOLT

13 NSA5539S 58 SLEEVE

14 ASNA2397-10L 35 WASHER

15 NSA5542-00 8 NUT

16 NSA5527-03-01 11 SPACER

17 NSA5527-03-10 1 SPACER

18 NSA5527-03-11 3 SPACER

19 NAS6603-24 2 BOLT

20 NAS6603-1 14 BOLT

21 NAS6603-9 9 BOLT

23 NAS6603-16 1 BOLT

26 NAS6603-32 1 BOLT

29 NAS6603-2 8 BOLT

30 NSA5546-00 2 ANGLE

34 F1131031621800 1 PLACARD

35 F1131031623800 1 PLACARD

36 F1131031623900 2 PLACARD

37 F1131031621900 2 PLACARD

38 F1131031624000 2 PLACARD

39 F1131031622000 2 PLACARD

40 F1131031622100 1 PLACARD

41 F1131031624100 1 PLACARD

79 F3611549100000 4 SUPPORT

80 F3611549500000 1 SUPPORT

81 F3611549600000 1 SUPPORT

103 35618-2-255 2 SNSGELEM

105 35598-2-255 1 SNSGELEM

114 35597-2-255 1 SNSGELEM

References

Fig. A-FBJAA

Installation of the New Sensing

Elements between FR44 and FR50 on

LH side

Sheet 01

Sheet 02

Sheet 03

Sheet 04

(a) Install the sensing elements and the supports between FR44 and FR46.

1 Install the supports between FR44 and FR46 :

1 Support F3611549600000 Item 81

17 Clamp NSA5543-00 Item 10

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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9 Spacer NSA5527-03-01 Item 16

3 Spacer NSA5527-03-11 Item 18

21 Washer ASNA2397-10L Item 14

2 Bolt NAS6603-24 Item 19

5 Bolt NAS6603-1 Item 20

7 Bolt NAS6603-9 Item 21

1 Bolt NAS6603-16 Item 23

2 Bolt NAS6603-2 Item 29

2 Install the placards at FR44 :

1 Placard F1131031621800 Item 34

1 Placard F1131031623800 Item 35

1 Placard F1131031623900 Item 36

1 Placard F1131031621900 Item 37

3 Install the sensing elements between FR44 and FR46 :

FIN 99HF

1 Sensing Element 35618-2-255 Item 103

FIN 304HF

1 Sensing Element 35618-2-255 Item 103

34 Sleeve-Protective NSA5539S Item 13

4 Nut NSA5542-00 Item 15

(b) Install the sensing elements and the supports between FR46 and FR50.

1 Install the supports between FR46 and FR50 :

2 Angle NSA5546-00 Item 30

4 Rivet-Blind ASNA0342T04-01 Item 11

1 Support F3611549500000 Item 80

4 Support F3611549100000 Item 79

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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12 Clamp NSA5543-00 Item 10

2 Spacer NSA5527-03-01 Item 16

1 Spacer NSA5527-03-10 Item 17

14 Washer ASNA2397-10L Item 14

9 Bolt NAS6603-1 Item 20

2 Bolt NAS6603-9 Item 21

1 Bolt NAS6603-32 Item 26

6 Bolt NAS6603-2 Item 29

2 Install the placards between FR46 and FR50 :

1 Placard F1131031623900 Item 36

1 Placard F1131031621900 Item 37

2 Placard F1131031624000 Item 38

2 Placard F1131031622000 Item 39

1 Placard F1131031622100 Item 40

1 Placard F1131031624100 Item 41

3 Install the sensing elements between FR46 and FR50 :

FIN 100HF

1 Sensing Element 35597-2-255 Item 114

FIN 305HF

1 Sensing Element 35598-2-255 Item 105

24 Sleeve-Protective NSA5539S Item 13

4 Nut NSA5542-00 Item 15

NOTE: Secure the nuts Item 15 with wire-lock MS20995C32 Item 27.

(17) Subtask 364033-831-011-001 - Install the sensing elements and the supports

between FR50 and FR53.6.

Work Zones and Access Panels

Zone Access/Work location

190 Work location from Frame 50 to Frame 53.6

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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SERVICE BULLETIN

Manpower Resources

Manhours 21.00

Minimum number of person 1

Subtask elapsed time 21.00

Skills AIRFRAME

Material necessary to do the job

Kit 364033A01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

10 NSA5543-00 37 CLAMP

11 ASNA0342T04-01 6 BOLT

13 NSA5539S 74 SLEEVE

14 ASNA2397-10L 51 WASHER

15 NSA5542-00 6 NUT

16 NSA5527-03-01 16 SPACER

18 NSA5527-03-11 1 SPACER

20 NAS6603-1 23 BOLT

21 NAS6603-9 16 BOLT

22 NSA5527-03-15 1 SPACER

24 NAS6603-15 1 BOLT

25 NSA5545-00 1 ANGLE

28 NAS6603-12 1 BOLT

29 NAS6603-2 10 BOLT

30 NSA5546-00 2 ANGLE

40 F1131031622100 1 PLACARD

41 F1131031624100 1 PLACARD

42 F1131031622200 2 PLACARD

43 F1131031624200 2 PLACARD

44 F1131031620400 2 PLACARD

45 F1131031624300 2 PLACARD

70 F3611548300000 1 SUPPORT

72 F3611548700000 1 SUPPORT

73 F3611548500000 1 SUPPORT

74 F3611548900000 1 SUPPORT

75 F3611548400000 1 SUPPORT

76 F3611548200000 1 SUPPORT

77 F3611548620000 1 SUPPORT

79 F3611549100000 3 SUPPORT

82 F3611549400000 1 SUPPORT

83 F3611549800000 1 SUPPORT

84 F3611549300000 1 SUPPORT

104 35567-3-255 1 SNSGELEM

106 35595-2-255 3 SNSGELEM

107 35596-2-255 1 SNSGELEM

108 35568-4-255 1 SNSGELEM

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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References

Fig. A-FBKAA

Installation of the New Sensing

Elements between FR50 and FR53.6 on

LH side

Sheet 01

Sheet 02

Sheet 03

Sheet 04

(a) Install the sensing elements and the supports between FR50 and FR53.2.

1 Install the supports between FR50 and FR53.2 :

1 Support F3611548700000 Item 72

1 Support F3611548400000 Item 75

1 Support F3611549400000 Item 82

1 Angle NSA5546-00 Item 30

2 Rivet-Blind ASNA0342T04-01 Item 11

13 Clamp NSA5543-00 Item 10

7 Spacer NSA5527-03-01 Item 16

16 Washer ASNA2397-10L Item 14

9 Bolt NAS6603-1 Item 20

7 Bolt NAS6603-9 Item 21

2 Install the placards between FR50 and FR53.2 :

1 Placard F1131031622100 Item 40

1 Placard F1131031624100 Item 41

1 Placard F1131031622200 Item 42

1 Placard F1131031624200 Item 43

3 Install the sensing elements between FR50 and FR53.2 :

FIN 101HF

1 Sensing Element 35595-2-255 Item 106

FIN 306HF

1 Sensing Element 35595-2-255 Item 106

26 Sleeve-Protective NSA5539S Item 13

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SERVICE BULLETIN

2 Nut NSA5542-00 Item 15

NOTE: Secure the nuts Item 15 with wire-lock MS20995C32 Item 27.

(b) Install the sensing elements and the supports between FR53.2 and FR53.6.

1 Install the supports between FR53.2 and FR53.6 :

1 Support F3611548300000 Item 70

1 Support F3611548500000 Item 73

1 Support F3611548900000 Item 74

1 Support F3611548200000 Item 76

1 Support F3611548620000 Item 77

3 Support F3611549100000 Item 79

1 Support F3611549800000 Item 83

1 Support F3611549300000 Item 84

1 Angle NSA5545-00 Item 25

1 Angle NSA5546-00 Item 30

4 Rivet-Blind ASNA0342T04-01 Item 11

24 Clamp NSA5543-00 Item 10

9 Spacer NSA5527-03-01 Item 16

1 Spacer NSA5527-03-11 Item 18

1 Spacer NSA5527-03-15 Item 22

35 Washer ASNA2397-10L Item 14

14 Bolt NAS6603-1 Item 20

9 Bolt NAS6603-9 Item 21

1 Bolt NAS6603-15 Item 24

1 Bolt NAS6603-12 Item 28

10 Bolt NAS6603-2 Item 29

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2 Install the placards between FR53.2 and FR53.6 :

1 Placard F1131031622200 Item 42

1 Placard F1131031624200 Item 43

2 Placard F1131031620400 Item 44

2 Placard F1131031624300 Item 45

3 Install the sensing elements between FR53.2 and FR53.6 :

FIN 102HF

1 Sensing Element 35595-2-255 Item 106

FIN 307HF

1 Sensing Element 35596-2-255 Item 107

FIN 23HF

1 Sensing Element 35568-4-255 Item 108

FIN 308HF

1 Sensing Element 35567-3-255 Item 104

48 Sleeve-Protective NSA5539S Item 13

4 Nut NSA5542-00 Item 15

NOTE: Secure the nuts Item 15 with wire-lock MS20995C32 Item 27.

(18) Subtask 364033-831-012-001 - Install the sensing elements and the supports

between FR53.6 and FR55.

Work Zones and Access Panels

Zone Access/Work location

190 Work location from Frame 53.6 to Frame 55

Manpower Resources

Manhours 14.00

Minimum number of person 1

Subtask elapsed time 14.00

Skills AIRFRAME

Material necessary to do the job

Kit 364033A01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

10 NSA5543-00 27 CLAMP

11 ASNA0342T04-01 2 BOLT

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SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

13 NSA5539S 55 SLEEVE

14 ASNA2397-10L 32 WASHER

15 NSA5542-00 2 NUT

16 NSA5527-03-01 6 SPACER

17 NSA5527-03-10 2 SPACER

18 NSA5527-03-11 5 SPACER

20 NAS6603-1 17 BOLT

21 NAS6603-9 1 BOLT

26 NAS6603-32 2 BOLT

29 NAS6603-2 2 BOLT

30 NSA5546-00 1 ANGLE

70 F3611548300000 1 SUPPORT

79 F3611549100000 1 SUPPORT

85 NSA5549-90 2 CONNECTR

86 NSA5538-00 3 CLAMP

87 NAS6603-17 5 BOLT

88 F1131031620500 1 PLACARD

89 F1131031624400 1 PLACARD

90 F1131031620600 1 PLACARD

91 F1131031624500 1 PLACARD

93 F3611549200095 1 SUPPORT

94 NAS6603-10 5 BOLT

95 F3611549000000 1 SUPPORT

109 35597-3-255 1 SNSGELEM

110 35587-2-255 1 SNSGELEM

111 35627-2-255 1 SNSGELEM

112 35625-2-255 1 SNSGELEM

References

Fig. A-FBLAA

Installation of the New Sensing

Elements between FR53.6 and FR55 on

LH side

Sheet 01

Sheet 02

Sheet 03

Sheet 04

(a) Install the sensing elements and the supports between FR53.6 and FR55.

1 Install the supports between FR53.6 and FR55 :

1 Support F3611548300000 Item 70

1 Support F3611549100000 Item 79

1 Support F3611549200095 Item 93

1 Support F3611549000000 Item 95

1 Angle NSA5546-00 Item 30

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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SERVICE BULLETIN

2 Rivet-Blind ASNA0342T04-01 Item 11

27 Clamp NSA5543-00 Item 10

3 Clamp NSA5538-00 Item 86

6 Spacer NSA5527-03-01 Item 16

2 Spacer NSA5527-03-10 Item 17

5 Spacer NSA5527-03-11 Item 18

32 Washer ASNA2397-10L Item 14

17 Bolt NAS6603-1 Item 20

1 Bolt NAS6603-9 Item 21

2 Bolt NAS6603-32 Item 26

2 Bolt NAS6603-2 Item 29

5 Bolt NAS6603-17 Item 87

5 Bolt NAS6603-10 Item 94

2 Install the placards between FR53.6 and FR55 :

1 Placard F1131031620500 Item 88

1 Placard F1131031624400 Item 89

1 Placard F1131031620600 Item 90

1 Placard F1131031624500 Item 91

3 Install the sensing elements between FR53.6 and FR55 :

FIN 24HF

1 Sensing Element 35597-3-255 Item 109

FIN 311HF

1 Sensing Element 35587-2-255 Item 110

FIN 25HF

1 Sensing Element 35627-2-255 Item 111

FIN 312HF

1 Sensing Element 35625-2-255 Item 112

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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2 Nut NSA5542-00 Item 15

2 Connector NSA5549-90 Item 85

55 Sleeve-Protective NSA5539S Item 13

NOTE: Secure the nuts Item 15 with wire-lock MS20995C32 Item 27.

(19) Subtask 364033-010-004-001 - If necessary, remove the ducts between FR39 and

FR40 for access.

Work Zones and Access Panels

Zone Access/Work location

190

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills AIRFRAME

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-010-801

Fig. A-FBPAA

Removal/Installation of the Ducts

Between FR39 and FR40 for Access

Sheet 01

(a) Remove :

Fig. A-FBPAA

(Refer to AMM Task 21-20-00-010-801)

1 Duct assy Item (125) Retain

1 Duct assy Item (126) Retain

1 Duct assy Item (127) Retain

(20) Subtask 364033-831-013-001 - Install the new supports for the new harness

between FR39.1 and FR39.2.

Work Zones and Access Panels

Zone Access/Work location

190

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 215

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SERVICE BULLETIN

Manpower Resources

Manhours 3.00

Minimum number of person 1

Subtask elapsed time 3.00

Skills AIRFRAME

Material necessary to do the job

Kit 364033A01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

63 ASNA2327-3-8 2 SUPPORT

64 F5391094700095 1 PLATE

65 NSA5456-3-8 1 SUPPORT

97 ASNA2050DCJ3215 14 RIVET

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Corrosion Inhibiting Brush

Consistency

09-013B As required

References

Fig. A-FBNAA

Installation of the Supports for the New

Harness

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

(a) At FR39.1, remove a support between STGR 37 and STGR 38.

Fig. A-FBNAA Sheet 02 and Fig. A-FBNAA Sheet 03

1 Remove :

2 Rivet Item (97) Discard

1 Support Item (88) Retain

2 Install :

2 Rivet ASNA2050DCJ3215 Item 97

NOTE: Wet install the fasteners with :

Corrosion Inhibiting

Brush Consistency

09-013B As required

(b) At FR39.1, install a support between STGR 37 and STGR 38.

Fig. A-FBNAA Sheet 02 and Fig. A-FBNAA Sheet 03

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1 Put the support Item (88) in position as shown on Fig. A-FBNAA Sheet 03.

2 Drill two holes on the structure to a diameter comprised between 3.25mm

(0.128in.) and 3.35mm (0.132in.) to match the holes of the support Item (88).

3 Install :

1 Support Item (88) Retained at

removal

2 Rivet ASNA2050DCJ3215 Item 97

NOTE: Wet install the fasteners with :

Corrosion Inhibiting

Brush Consistency

09-013B As required

(c) At FR39.2, install a plate between STGR 46 and STGR 47.

Fig. A-FBNAA Sheet 02 and Fig. A-FBNAA Sheet 04

1 Remove :

2 Rivet Item (97) Discard

1 Support Item (89) Retain

2 Put the plate Item 64 in position as shown on Fig. A-FBNAA Sheet 04.

3 Drill one hole on the plate Item 64 to a diameter comprised between 3.25mm

(0.128in.) and 3.35mm (0.132in.) to match the hole of the structure.

4 Drill three holes on the structure to a diameter comprised between 3.25mm

(0.128in.) and 3.35mm (0.132in.) to match the holes of the plate Item (64).

5 Install :

1 Plate F5391094700095 Item 64

4 Rivet ASNA2050DCJ3215 Item 97

NOTE: Wet install the fasteners with :

Corrosion Inhibiting

Brush Consistency

09-013B As required

(d) At FR39.2, install two supports between STGR46 and STGR48.

Fig. A-FBNAA Sheet 02 and Fig. A-FBNAA Sheet 04

1 Put the supports Item 63 in position as shown on Fig. A-FBNAA Sheet 04.

2 Drill four holes on the structure to a diameter comprised between 3.25mm

(0.128in.) and 3.35mm (0.132in.) to match the holes of the supports Item 63.

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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3 Install :

2 Support ASNA2327-3-8 Item 63

4 Rivet ASNA2050DCJ3215 Item 97

NOTE: Wet install the fasteners with :

Corrosion Inhibiting

Brush Consistency

09-013B As required

(e) At FR39.1, install a support between STGR 39 and STGR 40.

Fig. A-FBNAA Sheet 02 and Fig. A-FBNAA Sheet 05

1 Put the support Item 65 in position as shown on Fig. A-FBNAA Sheet 05.

2 Drill two holes on the structure to a diameter comprised between 3.25mm

(0.128in.) and 3.35mm (0.132in.) to match the holes of the support Item 65.

3 Install :

1 Support NSA5456-3-8 Item 65

2 Rivet ASNA2050DCJ3215 Item 97

NOTE: Wet install the fasteners with :

Corrosion Inhibiting

Brush Consistency

09-013B As required

(21) Subtask 364033-831-014-001 - Install the Interconnecting Electrical Wire FIN 309HF

and 310HF, between the sensing elements.

Work Zones and Access Panels

Zone Access/Work location

150

Manpower Resources

Manhours 3.00

Minimum number of person 1

Subtask elapsed time 3.00

Skills NON SPECIFIC

Material necessary to do the job

Kit 364033A02R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

14 ASNA2397-10L 1 WASHER

18 NSA5527-03-11 1 SPACER

92 NSA57304-643ADL 1 PLATE

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

155 NSA5516-04ND 1 CLAMP

168 NAS1801-3-22 1 SCREW

169 NSA935401-03 8 TIE

174 35301-74 1 CABLE

175 35301-75 2 CABLE

182 NSA5050-4 1 NUT

F1131031521900 1 PLACARD

F1131031522000 1 PLACARD

F9000095227895 BUNDLE

F9100095005595 1 PLACARD

References

Fig. A-FBCAA

Drilling of a New Hole in the Structure

between FR53.5 and FR53.6 on the LH

side and Installation of Sensing

Elements

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Fig. A-FCCAA

Installation of the Wiring of the New

Sensing Elements

Sheet 01

Sheet 02

(a) Put in position :

FIN 309HF

1 Cable-Electrical

Interconnecting

35301-74 Item 174

(b) Put in position :

FIN 310HF

1 Cable-Electrical

Interconnecting

35301-75 Item 175

(c) Install the splice FIN 3593VS (PN E0360RK1816) between the FIN 309HF and the

FIN 310HF, supplied in :

Bundle F9000095227895

(d) Identify the splice FIN 3593VS with the identification sleeves and the identification

label supplied in :

1 Placard F9100095005595

and

Bundle F9000095227895

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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(e) On the fuselage close to the plugs, identify the FIN 309HF and the FIN 310HF with

:

1 Placard F1131031521900

and

1 Placard F1131031522000

(f) Identify the wire No. 3622-0543 of the FIN 310HF and the wire No. 3622-0544 of

the FIN 309HF with the identification sleeves supplied in :

1 Placard F9100095005595

(g) Modify the splice FIN 3503VS :

1 Before any disconnection, record the wires number associated to the FIN

137HF and the FIN 138HF.

2 Remove the splice FIN 3503VS between the FIN 137HF and the FIN 138HF :

FIN 3503VS

1 Splice Discard

NOTE: Retain the identification sleeves and the identification label of

the 3503VS and of the wires associated to the FIN 137HF and

the FIN 138HF.

3 Remove :

FIN 137HF

1 Cable-Electrical

Interconnecting

35301-74 Item (174) Discard

4 Maintain in position :

FIN 138HF

1 Cable-Electrical

Interconnecting

35301-75 Item (175)

5 Put in position :

FIN 137HF

1 Cable-Electrical

Interconnecting

35301-75 Item 175

6 Install the new splice FIN 3503VS (PN E0360RK1816) between the FIN

137HF and the FIN 138HF, supplied in :

Bundle F9000095227895

NOTE: Identify the splice FIN 3503VS with the identification sleeves

and the identification label retained at removal.

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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NOTE: In accordance to the wires connections recorded at removal,

identify the wires associated to the FINs 137HF and 138HF

with the retained identification sleeves.

(h) Between Frame 53.5 and Frame 53.6 and as shown in Fig. A-FBCAA Sheet 01 and

Fig. A-FBCAA Sheet 03, install the FINs 137HF and 138HF and the FINs 309HF

and 310HF (spliced previously) with :

1 Spacer NSA5527-03-11 Item 18

1 Clamp NSA5516-04ND Item (155) Retained at

removal

1 Clamp NSA5516-04ND Item 155

1 Washer ASNA2397-10L Item 14

1 Screw NAS1801-3-22 Item 168

and attach it with :

8 Tie-Cable NSA935401-03 Item 169

NOTE: After connection, secure the FINs 137HF and 138HF and the FINs

309HF and 310HF with Wire-lock MS20995C32 item 27, (Refer to

Fig. A-FBCAA Sheet 05).

(i) Secure the FIN 310HF :

Refer to Fig. A-FBCAA Sheet 04

1 Remove :

1 Nut Discard

2 Install :

1 Plate-Attachment NSA57304-643ADL Item 92

With :

1 Nut NSA5050-4 Item 182

3 Secure the new nut and the FIN 310HF with wire-lock MS20995C32 item 27,

(Refer to Fig. A-FBCAA Sheet 05).

(22) Subtask 364033-831-015-001 - Install the new Harness 2SG.

Work Zones and Access Panels

Zone Access/Work location

190

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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SERVICE BULLETIN

Manpower Resources

Manhours 26.00

Minimum number of person 2

Subtask elapsed time 13.00

Skills NON SPECIFIC

Material necessary to do the job

Kit 364033A02R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

14 ASNA2397-10L 4 WASHER

16 NSA5527-03-01 2 SPACER

18 NSA5527-03-11 1 SPACER

22 NSA5527-03-15 1 SPACER

131 NSA935808-03 24 WASHER

134 NSA935807-16 1 CLAMP

135 NSA935807-20 1 CLAMP

141 NSA5527-03-02 3 SPACER

150 NSA935807-04 30 CLAMP

151 NSA5159-17 19 STUD

152 NSA5527-03-08 19 SPACER

153 NSA935808-01 13 WASHER

154 NSA5050-3 28 NUT

157 NSA5159-10 1 STUD

158 NAS1801-3-9 4 SCREW

159 NAS1801-3-8 2 SCREW

163 NSA5159-27 5 STUD

165 NSA5527-03-05 1 SPACER

166 NAS1801-3-12 4 SCREW

167 NAS1801-3-10 3 SCREW

170 MS21042-3 4 NUT

171 NAS1801-3-17 2 SCREW

172 NAS1149F0332P 2 WASHER

173 NSA5527-03-12 6 SPACER

174 35301-74 1 CABLE

176 NSA5516-21ND 5 CLAMP

177 NSA5516-22ND 5 CLAMP

178 NSA5516-23ND 5 CLAMP

179 NSA5516-07ND 2 CLAMP

180 NSA5516-08ND 2 CLAMP

181 NSA5516-10ND 2 CLAMP

183 NSA934710E20 3 SPRING

184 NSA934710T11 2 FITTING

E0432A04 20 (M) CONDUIT

F1131031522100 1 PLACARD

F9000095227895 BUNDLE

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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SERVICE BULLETIN

References

Elec. Std. Practices Manual (ESPM) 20-43-42

Fig. A-FBMAA

Installation of the New Harness 2SG

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

Sheet 09

Sheet 10

Sheet 11

Sheet 12

Sheet 13

Sheet 14

Sheet 15

Sheet 16

Sheet 17

Sheet 18

Sheet 19

Sheet 20

Sheet 21

Sheet 22

Fig. A-FCCAA

Installation of the Wiring of the New

Sensing Elements

Sheet 01

Sheet 02

(a) Install supports of new routing between 302HF located on the left hand side at

stringer 36 and Frame 40 and the 3520VP located on the right hand side at Frame

39.1 :

1 On the left hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03, Fig. A-FBMAA Sheet 04, Fig. A-FBMAA Sheet 05 and Fig. AFBMAA Sheet 06, along the Frame 39.1 and between Frame 39.1 and Frame

39.2, remove :

a For Section A-A :

7 Screw Item (130) Discard

7 Washer Item (131) Discard

7 Clamp Item (150) Retain

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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2 On the left hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03, Fig. A-FBMAA Sheet 04, Fig. A-FBMAA Sheet 05 and Fig. AFBMAA Sheet 06, along the Frame 39.1 and between Frame 39.1 and Frame

39.2, install :

a For Section B-B :

7 Stud NSA5159-17 Item 151

7 Clamp Item (150) Retained at

removal

7 Spacer NSA5527-03-08 Item 152

7 Clamp NSA935807-04 Item 150

7 Washer NSA935808-03 Item 131

7 Nut NSA5050-3 Item 154

b For Section C-C :

1 Stud NSA5159-17 Item 151

1 Clamp NSA935807-04 Item 150

1 Spacer NSA5527-03-08 Item 152

1 Clamp NSA935807-04 Item 150

1 Washer NSA935808-03 Item 131

1 Nut NSA5050-3 Item 154

NOTE: Install this hardware on the support Item 65 installed

previously.

3 On the left hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03, Fig. A-FBMAA Sheet 04, Fig. A-FBMAA Sheet 05 , Fig. A-FBMAA

Sheet 07, Fig. A-FBMAA Sheet 08 and Fig. A-FBMAA Sheet 09, along the

Frame 39.1 and between Stringer 39 and 40, remove :

a For Section F-F :

1 Screw Item (130) Discard

1 Washer Item (131) Discard

1 Clamp Item (150) Retain

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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SERVICE BULLETIN

b For Section G-G :

1 Screw Item (132) Discard

1 Washer Item (133) Discard

1 Clamp Item (155) Retain

4 On the left hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03, Fig. A-FBMAA Sheet 04, Fig. A-FBMAA Sheet 05 , Fig. A-FBMAA

Sheet 07, Fig. A-FBMAA Sheet 08 and Fig. A-FBMAA Sheet 09, along the

Frame 39.1 and between Stringer 39 and 40, install :

a For Section H-H :

1 Stud NSA5159-17 Item 151

1 Clamp Item (150) Retained at

removal

1 Spacer NSA5527-03-08 Item 152

1 Clamp NSA935807-04 Item 150

1 Washer NSA935808-03 Item 131

1 Nut NSA5050-3 Item 154

b For Section J-J :

1 Stud NSA5159-17 Item 151

1 Clamp Item (155) Retained at

removal

1 Spacer NSA5527-03-08 Item 152

1 Clamp NSA935807-04 Item 150

1 Washer NSA935808-03 Item 131

1 Nut NSA5050-3 Item 154

5 On the left hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 09, along the Frame 39.1 and between

Stringer 40 and 43, remove for detail F :

2 Screw Item (136) Discard

2 Washer Item (137) Discard

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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SERVICE BULLETIN

2 Clamp Item (135) Retain

2 Clamp Item (134) Retain

6 On the left hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 09, along the Frame 39.1 and between

Stringer 40 and 43, install for detail G :

2 Stud NSA5159-17 Item 151

2 Clamp Item (134) Retained at

removal

2 Clamp Item (135) Retained at

removal

2 Spacer NSA5527-03-08 Item 152

2 Clamp NSA935807-04 Item 150

2 Washer NSA935808-03 Item 131

2 Nut NSA5050-3 Item 154

7 On the left hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03, Fig. A-FBMAA Sheet 10 and Fig. A-FBMAA Sheet 11, along the

Frame 39.1 and between Stringers 44 and 45, remove :

a For Section K-K :

1 Nut Item (154) Discard

1 Washer Item (153) Discard

1 Clamp Item (138) Retain

1 Spacer Item (152) Retain

1 Clamp Item (135) Retain

1 Clamp Item (134) Retain

1 Stud Item (151) Retain

Or

1 Nut Item (154) Discard

1 Washer Item (153) Discard

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 226

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SERVICE BULLETIN

1 Clamp Item (138) Retain

1 Clamp Item (139) Retain

1 Spacer Item (152) Discard

1 Clamp Item (135) Retain

1 Clamp Item (134) Retain

1 Stud Item (151) Discard

8 On the left hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03, Fig. A-FBMAA Sheet 10 and Fig. A-FBMAA Sheet 11, along the

Frame 39.1 and between Stringers 44 and 45, install :

a For Section M-M :

1 Stud Item (151) Retained at

removal

1 Clamp Item (134) Retained at

removal

1 Clamp Item (135) Retained at

removal

1 Spacer Item (152) Retained at

removal

1 Clamp Item (138) Retained at

removal

1 Clamp NSA935807-04 Item 150

1 Washer NSA935808-03 Item 131

1 Nut NSA5050-3 Item 154

Or

1 Stud NSA5159-27 Item 163

1 Clamp Item (134) Retained at

removal

1 Clamp Item (135) Retained at

removal

2 Spacer NSA5527-03-12 Item 173

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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SERVICE BULLETIN

1 Clamp Item (139) Retained at

removal

1 Clamp Item (138) Retained at

removal

1 Clamp NSA935807-04 Item 150

1 Washer NSA935808-03 Item 131

1 Nut NSA5050-3 Item 154

9 On the left hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03, Fig. A-FBMAA Sheet 10 and Fig. A-FBMAA Sheet 12, along the

Frame 39.1 and between Stringers 44 and 45, remove :

a For Section L-L :

1 Screw Item (130) Discard

1 Washer Item (153) Discard

1 Clamp Item (135) Retain

1 Clamp Item (134) Retain

10 On the left hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03, Fig. A-FBMAA Sheet 10 and Fig. A-FBMAA Sheet 12, along the

Frame 39.1 and between Stringers 44 and 45, install :

a For Section N-N :

1 Stud NSA5159-17 Item 151

1 Clamp Item (134) Retained at

removal

1 Clamp Item (135) Retained at

removal

1 Spacer NSA5527-03-08 Item 152

1 Clamp NSA935807-04 Item 150

1 Washer NSA935808-03 Item 131

1 Nut NSA5050-3 Item 154

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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SERVICE BULLETIN

11 On the left hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03, Fig. A-FBMAA Sheet 13 and Fig. A-FBMAA Sheet 14, along the

Frame 39.1 and between Stringers 46 and 48, remove :

a For Section P-P :

1 Nut Item (154) Discard

1 Washer Item (153) Discard

1 Clamp Item (139) Retain

1 Spacer Item (152) Retain

1 Clamp Item (135) Retain

1 Clamp Item (134) Retain

1 Stud Item (151) Discard

Or

1 Nut Item (154) Discard

1 Washer Item (153) Discard

1 Clamp Item (138) Retain

1 Clamp Item (139) Retain

1 Spacer Item (152) Discard

1 Clamp Item (135) Retain

1 Clamp Item (134) Retain

1 Stud Item (151) Discard

12 On the left hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03, Fig. A-FBMAA Sheet 13 and Fig. A-FBMAA Sheet 14, along the

Frame 39.1 and between Stringers 46 and 48, install :

a For Section R-R :

1 Stud NSA5159-17 Item 151

1 Clamp Item (134) Retained at

removal

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 229

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@A340

SERVICE BULLETIN

1 Clamp Item (135) Retained at

removal

1 Spacer Item (152) Retained at

removal

1 Clamp Item (139) Retained at

removal

1 Clamp NSA935807-04 Item 150

1 Washer NSA935808-03 Item 131

1 Nut NSA5050-3 Item 154

Or

1 Stud NSA5159-27 Item 163

1 Clamp Item (134) Retained at

removal

1 Clamp Item (135) Retained at

removal

2 Spacer NSA5527-03-12 Item 173

1 Clamp Item (139) Retained at

removal

1 Clamp Item (138) Retained at

removal

1 Clamp NSA935807-04 Item 150

1 Washer NSA935808-03 Item 131

1 Nut NSA5050-3 Item 154

13 On the left hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03, Fig. A-FBMAA Sheet 13 and Fig. A-FBMAA Sheet 15, along the

Frame 39.1 and between Stringers 46 and 48, remove :

a For Section Q-Q :

1 Nut Item (154) Discard

1 Washer Item (153) Discard

1 Clamp Item (135) Retain

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 230

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SERVICE BULLETIN

1 Spacer Item (152) Retain

1 Clamp Item (134) Retain

1 Clamp Item (139) Retain

1 Stud Item (151) Retain

Or

1 Nut Item (154) Discard

1 Washer Item (153) Discard

1 Clamp Item (138) Retain

1 Clamp Item (135) Retain

1 Spacer Item (152) Discard

1 Clamp Item (134) Retain

1 Clamp Item (139) Retain

1 Stud Item (144) Discard

14 On the left hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03, Fig. A-FBMAA Sheet 13 and Fig. A-FBMAA Sheet 15, along the

Frame 39.1 and between Stringers 46 and 48, install :

a For Section S-S :

1 Stud Item (151) Retained at

removal

1 Clamp NSA935807-04 Item 150

1 Clamp Item (134) Retained at

removal

1 Spacer Item (152) Retained at

removal

1 Clamp Item (139) Retained at

removal

1 Clamp Item (135) Retained at

removal

1 Washer NSA935808-01 Item 153

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 231

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SERVICE BULLETIN

1 Nut NSA5050-3 Item 154

Or

1 Stud NSA5159-27 Item 163

1 Clamp NSA935807-04 Item 150

1 Clamp Item (134) Retained at

removal

2 Spacer NSA5527-03-12 Item 173

1 Clamp Item (139) Retained at

removal

1 Clamp Item (138) Retained at

removal

1 Clamp Item (135) Retained at

removal

1 Washer NSA935808-01 Item 153

1 Nut NSA5050-3 Item 154

15 On the left hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 16, along the Frame 39.1 and between

Stringers 49 and 52, remove for detail K :

2 Screw Item (132) Discard

2 Washer Item (153) Discard

2 Clamp Item (138) Retain

16 On the left hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 16, along the Frame 39.1 and between

Stringers 49 and 52, install for detail L :

2 Stud NSA5159-17 Item 151

2 Clamp Item (138) Retained at

removal

2 Spacer NSA5527-03-08 Item 152

2 Clamp NSA935807-04 Item 150

2 Washer NSA935808-03 Item 131

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 232

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SERVICE BULLETIN

2 Nut NSA5050-3 Item 154

17 On the left hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 17, along the Frame 39.1 and between

Stringers 52 and 54, remove for Section T-T :

1 Nut Item (154) Discard

1 Washer Item (153) Discard

1 Clamp Item (138) Retain

1 Spacer Item (141) Retain

1 Clamp Item (138) Retain

1 Stud Item (140) Retain

18 On the left hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 17, along the Frame 39.1 and between

Stringers 52 and 54, install for Section U-U :

1 Stud Item (140) Retained at

removal

1 Clamp Item (138) Retained at

removal

1 Spacer Item (141) Retained at

removal

1 Clamp Item (138) Retained at

removal

1 Clamp NSA935807-04 Item 150

1 Washer NSA935808-03 Item 131

1 Nut NSA5050-3 Item 154

19 On the right hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 18, along the Frame 39.1 and near the

Stringers 54, remove for detail N :

1 Screw Item (142) Discard

1 Washer Item (153) Discard

1 Clamp Item (138) Retain

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 233

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SERVICE BULLETIN

20 On the right hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 18, along the Frame 39.1 and near the

Stringers 54, install for detail P :

1 Stud NSA5159-17 Item 151

1 Clamp Item (138) Retained at

removal

1 Spacer NSA5527-03-08 Item 152

1 Clamp NSA935807-04 Item 150

1 Washer NSA935808-03 Item 131

1 Nut NSA5050-3 Item 154

21 On the right hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 18, along the Frame 39.1 and between

Stringers 54 and 48, remove for detail Q :

3 Screw Item (142) Discard

3 Washer Item (153) Discard

3 Clamp Item (138) Retain

22 On the right hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 18, along the Frame 39.1 and between

Stringers 54 and 48, install for detail R :

3 Clamp NSA935807-04 Item 150

3 Clamp Item (138) Retained at

removal

3 Washer NSA935808-01 Item 153

3 Screw NAS1801-3-9 Item 158

23 On the right hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 18, between the Frame 39.1 and Frame

39.2 and between Stringers 48 and 46, install for detail S :

2 Clamp NSA935807-04 Item 150

2 Washer NSA935808-03 Item 131

2 Screw NAS1801-3-8 Item 159

NOTE: Install this hardware on the support Item 63 installed

previously.

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 234

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SERVICE BULLETIN

24 On the right hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 19, between the Frame 39.1 and Frame

39.2 and between Stringers 48 and 46, install for Section W-W :

2 Spacer NSA5527-03-02 Item 141

2 Clamp NSA5516-07ND Item 179

or

2 Clamp NSA5516-08ND Item 180

or

2 Clamp NSA5516-10ND Item 181

and

2 Washer NAS1149F0332P Item 172

2 Screw NAS1801-3-17 Item 171

NOTE: Depends on aircraft configuration, use the PN NSA5516-07ND

or NSA5516-08ND or NSA5516-10ND for Item 170.

NOTE: Install this hardware on the support Item 64 installed

previously.

25 On the right hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 19, between the Frame 39.1 and Frame

39.2 and between Stringers 48 and 46, install for Section V-V :

1 Stud NSA5159-27 Item 163

1 Spacer NSA5527-03-01 Item 16

1 Clamp NSA935807-16 Item 134

1 Spacer NSA5527-03-08 Item 152

1 Clamp NSA935807-20 Item 135

1 Washer NSA935808-01 Item 153

1 Nut NSA5050-3 Item 154

NOTE: Install this hardware on the support Item 64 installed

previously.

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 235

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SERVICE BULLETIN

26 On the right hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 20, between the Frame 39.1 and Frame

39.2 and between Stringers 47 and 46, remove for detail T :

1 Screw Item (136) Discard

1 Washer Item (153) Discard

1 Clamp Item (135) Retain

1 Clamp Item (134) Retain

27 On the right hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 20, between the Frame 39.1 and Frame

39.2 and between Stringers 47 and 46, install for detail U :

1 Stud NSA5159-17 Item 151

1 Spacer NSA5527-03-02 Item 141

1 Clamp Item (134) Retained at

removal

1 Spacer NSA5527-03-05 Item 165

1 Clamp Item (135) Retained at

removal

1 Washer NSA935808-01 Item 153

1 Nut NSA5050-3 Item 154

28 On the right hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 20, between the Frame 39.1 and Frame

39.2 and between Stringers 47 and 46, remove for detail Y :

1 Screw Item (143) Discard

1 Washer Item (133) Discard

1 Clamp Item (155) Retain

1 Clamp Item (155) Retain

29 On the right hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 20, between the Frame 39.1 and Frame

39.2 and between Stringers 47 and 46, install for detail Z :

1 Stud NSA5159-27 Item 163

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 236

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SERVICE BULLETIN

1 Clamp Item (155) Retained at

removal

1 Clamp Item (155) Retained at

removal

1 Spacer NSA5527-03-08 Item 152

1 Spacer NSA5527-03-15 Item 22

1 Clamp NSA935807-04 Item 150

1 Washer NSA935808-03 Item 131

1 Nut NSA5050-3 Item 154

30 On the right hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 20, between the Frame 39.1 and Frame

39.2 and between Stringers 46 and 45, remove for detail W :

1 Screw Item (136) Discard

1 Washer Item (153) Discard

1 Clamp Item (135) Retain

1 Clamp Item (134) Discard

31 On the right hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 20, between the Frame 39.1 and Frame

39.2 and between Stringers 46 and 45, install for detail X :

1 Stud NSA5159-10 Item 157

And

1 Clamp NSA5516-21ND Item 176

Or

1 Clamp NSA5516-22ND Item 177

Or

1 Clamp NSA5516-23ND Item 178

And

1 Spacer NSA5527-03-01 Item 16

1 Spacer NSA5527-03-08 Item 152

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 237

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@A340

SERVICE BULLETIN

1 Clamp Item (135) Retained at

removal

1 Washer NSA935808-01 Item 153

1 Nut NSA5050-3 Item 154

NOTE: Depends on aircraft configuration, use the PN NSA5516-21ND

or NSA5516-22ND or NSA5516-23ND for Item 166.

32 On the right hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 21, between the Frame 39.1 and Frame

39.2 and between Stringers 44 and 43, remove for detail AA :

1 Screw Item (136) Discard

1 Washer Item (153) Discard

1 Clamp Item (135) Retain

1 Clamp Item (134) Discard

33 On the right hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 21, between the Frame 39.1 and Frame

39.2 and between Stringers 44 and 43, install for detail AB :

1 Stud NSA5159-17 Item 151

And

1 Clamp NSA5516-21ND Item 176

Or

1 Clamp NSA5516-22ND Item 177

Or

1 Clamp NSA5516-23ND Item 178

And

1 Spacer NSA5527-03-11 Item 18

1 Clamp Item (135) Retained at

removal

1 Washer NSA935808-01 Item 153

1 Nut NSA5050-3 Item 154

NOTE: Depends on aircraft configuration, use the PN NSA5516-21ND

or NSA5516-22ND or NSA5516-23ND for Item 166.

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 238

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SERVICE BULLETIN

34 On the right hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 21, between the Frame 39.1 and Frame

39.2 and between Stringers 42 and 38, remove for detail AC :

3 Screw Item (136) Discard

3 Washer Item (153) Discard

3 Clamp Item (135) Retain

3 Clamp Item (134) Discard

35 On the right hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 21, between the Frame 39.1 and Frame

39.2 and between Stringers 42 and 38, install for detail AD :

3 Clamp NSA5516-21ND Item 176

Or

3 Clamp NSA5516-22ND Item 177

Or

3 Clamp NSA5516-23ND Item 178

And

3 Clamp Item (135) Retained at

removal

3 Washer NSA935808-01 Item 153

3 Screw NAS1801-3-10 Item 167

NOTE: Depends on aircraft configuration, use the PN NSA5516-21ND

or NSA5516-22ND or NSA5516-23ND for Item 166.

36 On the right hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 21, along the Frame 39.1 and between

Stringers 38 and 37, remove for detail AE :

1 Screw Item (153) Discard

1 Washer Item (142) Discard

1 Clamp Item (135) Retain

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 239

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SERVICE BULLETIN

37 On the right hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 21, between the Frame 39.1 and Frame

39.2 and between Stringers 38 and 37, install for detail AF :

1 Clamp Item (135) Retained at

removal

1 Washer NSA935808-01 Item 153

1 Screw NAS1801-3-9 Item 158

NOTE: Install this hardware on the support Item (88) installed

previously.

(b) Install the new route 2SG between FIN 302HF located on the left hand side at

stringer 36 and Frame 40 and the FIN 3520VC located in the avionics compartment

:

1 Remove the pressure seal 3520VP :

Refer to ESPM 20-43-42 and to Fig. A-FBMAA Sheet 22

a Remove :

2 Fitting-Seal NSA934710T11 Item (184) Discard

And

3 Spring NSA934710E20 Item (183) Discard

Attached with :

4 Screw NAS1801-3-12 Item (166) Discard

4 Washer ASNA2397-10L Item (14) Discard

4 Nut MS21042-3 Item (170) Discard

2 Put in position :

FIN 301HF

1 Cable-Electrical

Interconnecting

35301-74 Item 174

3 Install :

20 (M) Conduit E0432A04

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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4 Using supports installed at paragraph 3.C.(20).(a), route the wire No.

3622-0540 spliced at paragraph 3.C.(20).(b).2, from FIN 301HF located on the

left hand side at stringer 36 and at Frame 40, through pressure seal 3520VP,

to 3520VC located in avionics compartment as shown in Fig. A-FCCAA Sheet

01 and in Fig. A-FBMAA Sheet 01.

NOTE: The route 2SG rejoins route 2S on the right hand side at

stringer 46 between Frame 39.1 and Frame 39.2 as shown in

Fig. A-FBMAA Sheet 17.

5 Connect the wire No. 3622-0540 as shown on the wiring diagram, Fig. AFCCAA Sheet 01 and as given in the Hook-up Chart lines :

- 1 and 2 (Refer to Fig. A-FCCAA Sheet 02).

NOTE: Use the contacts supplied in :

Bundle F9000095227895

6 Install the splice FIN 3591VS (PN NSA936809RG0002) between the FIN

301HF and the wire No. 3622-0540 supplied in :

Bundle F9000095227895

NOTE: After connection, Secure the FIN 301HF and FIN 302HF with

Wire-lock MS20995C32 item 27.

7 Install the pressure seal 3520VP :

Refer to ESPM 20-43-42 and to Fig. A-FBMAA Sheet 22

a Install :

2 Fitting-Seal NSA934710T11 Item 184

And

3 Spring NSA934710E20 Item 183

Attach with :

4 Screw NAS1801-3-12 Item 166

4 Washer ASNA2397-10L Item 14

4 Nut MS21042-3 Item 170

8 Identify the splice FIN 3591VS with the identification sleeves and the

identification label supplied in :

Bundle F9000095227895

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 241

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SERVICE BULLETIN

9 On the fuselage close to the plugs, identify the FIN 301HF with :

1 Placard F1131031522100

(23) Subtask 364033-831-201-003 - Install the electrical wiring in the FWD cargo

compartment

Work Zones and Access Panels

Zone Access/Work location

130 Work location from Frame 19 to Frame 37.1

Manpower Resources

Manhours 7.50

Minimum number of person 2

Subtask elapsed time 3.50

Skills ELECTRICAL

Material necessary to do the job

Kit 364033D01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

400 F9297000500000 1 EQUIPMNT

402 F9237000207400 2 PLCRDSET

404 NSA935401-03 100 TIE

405 NSA935401-04 100 TIE

406 NSA935401-05 100 TIE

407 NSA935401-10 100 TIE

References

Fig. A-GBAAB

Installation of the Electrical Wiring in the

FWD Cargo Compartment

Sheet 01

Fig. A-GHAAA

Hook-up Chart

Sheet 01

Fig. A-GHBAA

Hook-up Chart

Sheet 01

Fig. A-GWAAA

Wiring Diagram

Sheet 01

(a) Install the electrical wiring in the FWD cargo compartment

1 Install the electrical wires:

Refer to Fig. A-GBAAB Sheet 01

Refer to Fig. A-GHAAA Sheet 01, Line 1 thru 2, END 1,

Refer to Fig. A-GWAAA Sheet 01

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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supplied with:

1 Equipment AssyElectricalF9297000500000 Item 400

2 Attach the electrical wires with:

Refer to Fig. A-GBAAB Sheet 01

100 Tie-Cable NSA935401-03 Item 404

100 Tie-Cable NSA935401-04 Item 405

100 Tie-Cable NSA935401-05 Item 406

100 Tie-Cable NSA935401-10 Item 407

Install the identification placards

2 Placard Set F9237000207400 Item 402

(24) Subtask 364033-831-202-001 - Install the electrical wiring in the AFT cargo

compartment and Bulk cargo compartment

Work Zones and Access Panels

Zone Access/Work location

From 150 Work location Frame 55

To 170 Work location Frame 80

Manpower Resources

Manhours 11.00

Minimum number of person 2

Subtask elapsed time 5.50

Skills ELECTRICAL

Material necessary to do the job

Kit 364033D01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

400 F9297000500000 1 EQUIPMNT

402 F9237000207400 4 PLCRDSET

404 NSA935401-03 100 TIE

405 NSA935401-04 100 TIE

406 NSA935401-05 100 TIE

407 NSA935401-10 100 TIE

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 243

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SERVICE BULLETIN

References

Fig. A-GBBAA

Installation of the Electrical Wiring in the

AFT Cargo Compartment

Sheet 01

Sheet 02

Fig. A-GHAAA

Hook-up Chart

Sheet 01

Fig. A-GHBAA

Hook-up Chart

Sheet 01

Fig. A-GWAAA

Wiring Diagram

Sheet 01

(a) Install the electrical wiring in the AFT cargo compartment and Bulk cargo

compartment

1 Install the electrical wires on 5866VB between Frame 55 thru Frame 80/82:

Refer to Fig. A-GBBAA Sheet 01

Refer to Fig. A-GWAAA Sheet 01

Refer to Fig. A-GHAAA Sheet 01, Line 1 thru 3, END 1,

supplied with:

1 Equipment AssyElectricalF9297000500000 Item 400

2 Attach the electrical wires with:

Refer to Fig. A-GBBAA Sheet 01

100 Tie-Cable NSA935401-03 Item 404

100 Tie-Cable NSA935401-04 Item 405

100 Tie-Cable NSA935401-05 Item 406

100 Tie-Cable NSA935401-10 Item 407

Install the identification placards

4 Placard Set F9237000207400 Item 402

3 Route the electrical wires through the thermal insulator at Frame 80/82:

Refer to Fig. A-GBBAA Sheet 02

1 Insulator-Cable

Protection

ABS0596S006 Item (403)

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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SERVICE BULLETIN

(25) Subtask 364033-831-203-001 - Modify the electrical wiring in the AFT cargo

compartment, Bulk cargo compartment and Rear fuselage section

Manpower Resources

Manhours 4.50

Minimum number of person 1

Subtask elapsed time 4.50

Skills ELECTRICAL

References

Fig. A-GBCAA

Preparation for the Electrical Wiring

Installation in the Rear Fuselage Section

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

Sheet 09

Sheet 10

Fig. A-GHAAA

Hook-up Chart

Sheet 01

Fig. A-GHBAA

Hook-up Chart

Sheet 01

(a) Remove the pressure seal 5208VP from the pressure Frame at Frame 80/82

Refer to Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet 03

Remove:

1 Plate F9249011000200 Item (410) Retain

1 Plate F9249011000400 Item (411) Retain

2 Bulkhead Item (415) Discard

8 Screw Item (416) Discard

12 Washer Item (417) Discard

4 Washer Item (418) Discard

4 Nut Item (419) Discard

or if alternate installed remove:

12 Washer Item (417) Discard

4 Washer Item (418) Discard

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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4 Nut Item (419) Discard

4 Screw Item (420) Discard

2 Screw Item (423) Discard

(b) Remove the lightning protection of the electrical bundle 5886VB at Frame 90

Refer to Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet 08

1 At Frame 90 loosen the electrical receptacle 5215VC, Item (435).

Refer to Fig. A-GBCAA Sheet 04 thru Fig. A-GBCAA Sheet 05

4 Screw Item (430) Discard

4 Washer Item (431) Discard

4 Nut Item (432) Discard

2 Disconnect the electrical wires end from the electrical receptacle 5215VC.

Refer to Fig. A-GBCAA Sheet 04 thru Fig. A-GBCAA Sheet 05

Refer to Fig. A-GHAAA Sheet 01 END 2, Line 4 thru 25 Fig. A-GHBAA Sheet

01 END 2, Line 1 and 2

Remove:

1 Receptacle Item (435) Retain

3 Remove from Frame 91

Refer to Fig. A-GBCAA Sheet 04 thru Fig. A-GBCAA Sheet 05

1 Screw Item (314) Discard

1 Washer Item (417) Discard

1 Clamp Item (437) Discard

1 Clip nut Item (353) Discard

4 Remove the lightning protection from the electrical bundle 5886VB at Frame

90

Refer to Fig. A-GBCAA Sheet 04 thru Fig. A-GBCAA Sheet 08

8 Screw Item (314) Discard

12 Washer Item (417) Discard

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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3 Nut Item (419) Discard

21 Clamp Item (437) Retain

3 Spacer Item (442) Retain

1 Clamp Item (443) Retain

4 Screw Item (444) Discard

1 Clip nut Item (448) Discard

or if alternate installed remove:

1 Washer Item (417) Discard

2 Spacer Item (442) Retain

3 Clamp Item (437) Retain

1 Clip nut Item (439) Discard

1 Screw Item (501) Discard

(c) Disconnect the electrical wiring 5865VB from the APU overhead leak detection

system at Frame 93

Refer to Fig. A-GBCAA Sheet 01, Fig. A-GBCAA Sheet 09 thru Fig. A-GBCAA

Sheet 10

Refer to Fig. A-GHAAA Sheet 01

1 Remove between Frame 92 thru Frame 93:

Refer to Fig. A-GBCAA Sheet 09 thru Fig. A-GBCAA Sheet 10

1 Washer Item (417) Discard

1 Nut Item (419) Discard

2 Clamp Item (437) Retain

1 Screw Item (449) Discard

1 Spacer Item (464) Retain

1 Screw Item (465) Discard

1 Nut Item (470) Discard

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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1 Washer Item (471) Discard

2 Remove from Frame 93:

Refer to Fig. A-GBCAA Sheet 09

2 Washer Item (417) Discard

4 Spacer Item (442) Retain

2 Clamp Item (437) Retain

2 Clip nut Item (448) Discard

2 Screw Item (501) Discard

3 Remove the electrical splice 5151VSA from Frame 93:

Refer to Fig. A-GBCAA Sheet 09 thru Fig. A-GBCAA Sheet 10

Refer to Fig. A-GHAAA Sheet 01 END 2, Line 4 and 5

1 Sleeve Item (479) Discard

1 Sleeve Item (480) Discard

1 Splice Item (481) Discard

(26) Subtask 364033-831-205-001 - Install an additional profile in the Rear fuselage

section

Work Zones and Access Panels

Zone Access/Work location

310 Work location from Frame 90 to Frame 91

Stringer 6RH

Manpower Resources

Manhours 3.00

Minimum number of person 1

Subtask elapsed time 3.00

Skills AIRFRAME

Material necessary to do the job

Kit 364033D03R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

314 NAS1801-3-8 2 SCREW

460 F5397083308600 1 SECTION

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 248

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ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

461 MS21047L3 1 NUT

462 EN6101AD3-08 2 RIVET

463 NAS1149D0332J 2 WASHER

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Corrosion Inhibitive interfay

Sealant

09-005

Corrosion Inhibiting, Fillet

Consistency

09-016 As required

Corrosion Inhibiting low

Adhesion Sealant

09-018

References

Fig. A-GBEAA

Installation of the Bracket between FR90

and FR91

Sheet 01

(a) Install an additional profile in the Rear fuselage section

1 Between Frame 90 thru Frame 91, at RH STGR6, temporarily put into position

Refer to Fig. A-GBEAA Sheet 01

1 Section Assy F5397083308600 Item 460

2 Transfer drill the holes and open holes to final dimension and install:

1 Nut MS21047L3 Item 461

with:

2 Rivet EN6101AD3-08 Item 462

NOTE: For dimensions refer to the table on Fig. A-GBEAA Sheet 01.

3 Between Frame 90 thru Frame 91, at RH STGR6, install:

1 Section Assy F5397083308600 Item 460

with:

2 Screw NAS1801-3-8 Item 314

2 Washer NAS1149D0332J Item 463

and protect the surface with:

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 249

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SERVICE BULLETIN

Corrosion Inhibitive

interfay Sealant

09-005 As required

and

Corrosion Inhibiting,

Fillet Consistency

09-016 As required

, and seal the edges with:

Corrosion Inhibiting

low Adhesion

Sealant

09-018 As required

(27) Subtask 364033-831-204-001 - Install the electrical wiring in the rear fuselage

section

Work Zones and Access Panels

Zone Access/Work location

310 Work location from Frame 80/82 to Frame 93

Manpower Resources

Manhours 14.00

Minimum number of person 2

Subtask elapsed time 7.00

Skills ELECTRICAL

Material necessary to do the job

Kit 364033D01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

314 NAS1801-3-8 8 SCREW

320 NSA5527-03-02 5 SPACER

350 AS21919WCH13 6 CLAMP

351 MS21919WCH14 1 CLAMP

352 MS21919WCH8 1 CLAMP

353 NSA5067-3-1 1 NUT

400 F9297000500000 1 EQUIPMNT

402 F9237000207400 10 PLCRDSET

404 NSA935401-03 100 TIE

405 NSA935401-04 100 TIE

406 NSA935401-05 50 TIE

415 NSA934710T14 2 FITTING

416 NAS1801-3-9 8 SCREW

417 NAS1149C0332R 24 WASHER

418 NAS1149D0363K 4 WASHER

419 NAS1291C3M 10 NUT

420 NAS1102-3-10 4 SCREW

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

423 NAS1801-3-10 2 SCREW

430 NAS1100-04-6 4 SCREW

431 NAS1149CN416R 4 WASHER

432 MS21042-04 4 NUT

439 NSA5066-3-1 1 NUT

444 NAS1801-3-18 3 SCREW

448 NSA5066-3-2 1 NUT

449 NAS1801-08-8 2 SCREW

451 F9249016013200 1 PROTSYS

465 NAS1801-3-15 1 SCREW

469 ASNA0182-4ADL 2 STRIP

470 NAS1291C08M 3 NUT

471 NAS1149CN816R 5 WASHER

472 ASNA0182-3ADL 1 STRIP

475 NAS1801-08-36 2 SCREW

476 NSA5066-08-1 2 NUT

479 E0718-01 0.06 TUBING

480 NSA937210MB0300 0.1 TUBING

481 NSA936809RG0001 2 SPLICE

485 NSA934710E20 3 SPRING

488 E0126-06L 0.2 TUBING

489 F9249016510800 1 PROTSYS

492 ABS0580A17P 1 FITTING

493 NAS1801-3-21 2 SCREW

494 NSA935808C03 2 WASHER

496 NSA5527-03-08D 2 SPACER

501 NAS1801-3-27 2 SCREW

510 E0126-01L 0.35 TUBING

511 F9249016110900 1 PROTSYS

515 AS21919WCH07 1 CLAMP

517 ABS0513-09 1 SUPPORT

518 ABS0520-07P 1 NUT

521 AS21919WCH14 1 CLAMP

528 NAS1801-08-12 1 SCREW

536 AS21919WCH02 3 CLAMP

537 AS21919WCH09 1 CLAMP

843 MS21919WCH12 1 CLAMP

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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References

Fig. A-GBDAA

Installation of the Electrical Wiring in the

Rear Fuselage Section

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

Sheet 09

Sheet 10

Sheet 11

(a) Install the electrical wire in the rear fuselage section

1 Install the electrical wire, Item 400, on 5866VB between Frame 80/82 thru

Frame 90

Refer to Fig. A-GBDAA Sheet 01

1 Equipment AssyElectricalF9297000500000 Item 400

Attach the wire with:

2 Placard Set F9237000207400 Item 402

100 Tie-Cable NSA935401-03 Item 404

100 Tie-Cable NSA935401-04 Item 405

50 Tie-Cable NSA935401-05 Item 406

2 Install the electrical wire on 5866VB with the pressure seal 5208VP at Frame

80/82

Refer to Fig. A-GBDAA Sheet 01 thru Fig. A-GBDAA Sheet 03

Install:

1 Plate F9249011000200 Item (410) Retained at

removal

1 Plate F9249011000400 Item (411) Retained at

removal

with:

2 Fitting-Seal NSA934710T14 Item 415

8 Screw NAS1801-3-9 Item 416

12 Washer NAS1149C0332R Item 417

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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4 Washer NAS1149D0363K Item 418

4 Nut NAS1291C3M Item 419

4 Screw NAS1102-3-10 Item 420

2 Screw NAS1801-3-10 Item 423

NOTE: Alternative to two of the, Item 416.

3 Spring NSA934710E20 Item 485

3 Install the lightning protection of the electrical bundle 5886VB at Frame 90.

Attach to the wires on 5866VB leaving thru the 3 way transition at Frame 90

Refer to Fig. A-GBDAA Sheet 04

0.1 Tubing-Heat-Shrinkable E0126-06L Item 488

NOTE: Cut the sleeve to the necessary length.

4 Route the wires on 5866VB between Frame 90 thru Frame 91

Refer to Fig. A-GBDAA Sheet 04, Fig. A-GBDAA Sheet 08 thru Fig. A-GBDAA

Sheet 09

Install:

1 Protection SystemLightningF9249016510800 Item 489

with:

1 Washer NAS1149C0332R Item 417

1 Screw NAS1801-3-18 Item 444

1 Clamp AS21919WCH13 Item 350

1 Clamp Item (437) Retained at

removal

1 Spacer Item (442) Retained at

removal

5 Route the electrical wires:

Refer to Fig. A-GBDAA Sheet 04 and Fig. A-GBDAA Sheet 08

1 Fitting-Conduit ABS0580A17P Item 492

and install, Item 492, at Frame 90 with:

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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1 Clamp MS21919WCH14 Item 351

2 Nut NAS1291C3M Item 419

1 Strip ASNA0182-4ADL Item 469

2 Screw NAS1801-3-21 Item 493

2 Washer NSA935808C03 Item 494

2 Spacer NSA5527-03-08D Item 496

1 Clamp MS21919WCH12 Item 843

6 Route the electrical wires on 5866VB between Frame 90 thru Frame 91 to

connector 5215VC

Refer to Fig. A-GBDAA Sheet 04 thru Fig. A-GBDAA Sheet 08

Reinstall the connector 5215VC

1 Receptacle Item (435) Retained at

removal

attached with:

4 Screw NAS1100-04-6 Item 430

4 Washer NAS1149CN416R Item 431

4 Nut MS21042-04 Item 432

and install:

1 Screw NAS1801-3-8 Item 314

1 Washer NAS1149C0332R Item 417

2 Clamp Item (437) Retained at

removal

1 Nut-Clip NSA5066-3-2 Item 448

or alternative install:

1 Washer NAS1149C0332R Item 417

3 Clamp Item (437) Retained at

removal

1 Nut-Clip NSA5066-3-1 Item 439

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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2 Spacer Item (442) Retained at

removal

1 Screw NAS1801-3-27 Item 501

and install:

12 Clamp Item (437) Retained at

removal

2 Spacer Item (442) Retained at

removal

5 Clamp AS21919WCH13 Item 350

8 Washer NAS1149C0332R Item 417

7 Screw NAS1801-3-8 Item 314

1 Screw NAS1801-3-27 Item 501

2 Spacer NSA5527-03-02 Item 320

3 Nut NAS1291C3M Item 419

2 Screw NAS1801-3-18 Item 444

1 Nut NSA5067-3-1 Item 353

7 Route the wire, Item 400, from the 3 way transition, Item 492, to the splice

5410VS and route to the wire 5866VB with:

Refer to Fig. A-GBDAA Sheet 04 and Fig. A-GBDAA Sheet 08

1 Protection SystemLightningF9249016013200 Item 451

1 Protection SystemLightningF9249016510800 Item 489

1 Protection SystemLightningF9249016110900 Item 511

0.1 Tubing-Heat-Shrinkable E0126-06L Item 488

0.35 Tubing-Heat-Shrinkable E0126-01L Item 510

NOTE: Cut the sleeve to the necessary length.

and install:

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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8 Placard Set F9237000207400 Item 402

8 Install the protection, Item 511, at Frame 93 with:

1 Nut ABS0520-07P Item 518

1 Support-Strain Relief ABS0513-09 Item 517

9 Install the electrical wire at Frame 93on 5865VB and 5866VB with:

Refer to Fig. A-GBDAA Sheet 01 and Fig. A-GBDAA Sheet 10 thru Fig. AGBDAA Sheet 11

Install:

3 Spacer NSA5527-03-02 Item 320

1 Clamp MS21919WCH8 Item 352

1 Washer NAS1149C0332R Item 417

1 Nut NAS1291C3M Item 419

6 Clamp Item (437) Retained at

removal

5 Spacer Item (442) Retained at

removal

2 Screw NAS1801-08-8 Item 449

1 Screw NAS1801-3-15 Item 465

1 Strip ASNA0182-4ADL Item 469

3 Nut NAS1291C08M Item 470

5 Washer NAS1149CN816R Item 471

1 Strip-Bonding ASNA0182-3ADL Item 472

2 Screw NAS1801-08-36 Item 475

2 Nut-Clip NSA5066-08-1 Item 476

1 Clamp AS21919WCH07 Item 515

1 Clamp AS21919WCH14 Item 521

1 Screw NAS1801-08-12 Item 528

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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3 Clamp AS21919WCH02 Item 536

1 Clamp AS21919WCH09 Item 537

for the wire connection install:

0.06 Tubing-Heat-Shrinkable E0718-01 Item 479

0.1 Tubing-Heat Shrink NSA937210MB0300 Item 480

2 Splice NSA936809RG0001 Item 481

(28) Subtask 364033-831-206-002 - Remove the sensing elements in the AFT and Bulk

cargo compartments

Work Zones and Access Panels

Zone Access/Work location

From 160 Work location Frame 55

To 310 Work location Frame 83

Manpower Resources

Manhours 5.25

Minimum number of person 1

Subtask elapsed time 5.25

Skills ELECTRICAL

References

Fig. A-GBFAB

Removal of the Sensing Elements in the

Bulk and AFT Cargo Compartments

Sheet 01

Sheet 02

Sheet 03

(a) Remove the sensing elements in the AFT and Bulk cargo compartments

1 Remove the sensing elements between Frame 55 thru Frame 83

Refer to Fig. A-GBFAB Sheet 01 thru Fig. A-GBFAB Sheet 03

Remove:

FIN 26HF

1 Sensing Element 35593-2-255 Item (358)

FIN 27HF

1 Sensing Element 35609-2-255 Item (562)

FIN 28HF

1 Sensing Element 35593-2-255 Item (564)

FIN 29HF

1 Sensing Element 35593-2-255 Item (566)

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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FIN 30HF

1 Sensing Element 35609-2-255 Item (563)

FIN 31HF

1 Sensing Element 35609-2-255 Item (570)

FIN 32HF

1 Sensing Element 35609-2-255 Item (572)

attached with:

7 Nut Item (599) Retain

7 Flange Item (592) Discard

17 Sleeve Item (602) Discard

17 Clamp Item (357) Discard

10 Screw Item (620) Retain

10 Spacer Item (609) Discard

16 Clip Nut Item (399) Retain

16 Screw Item (601) Retain

2 Remove the connector of the sensing element at Frame 80/82

Refer to Fig. A-GBFAB Sheet 01 and Fig. A-GBFAB Sheet 03

Remove:

1 Connector Item (355) Discard

2 Washer Item (596) Discard

1 Washer Item (597) Discard

(29) Subtask 364033-831-212-001 - Drill an additional hole for the dual loop overheat

leak detection in the sheet metal pressure bulkhead

Manpower Resources

Manhours 0.75

Minimum number of person 1

Subtask elapsed time 0.75

Skills AIRFRAME

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 258

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SERVICE BULLETIN

References

Fig. A-GBMAA

Hole Location and Dimensions for the

sensing element Installation in the Sheet

Metal Pressure Bulkhead

Sheet 01

(a) Drill the hole for the dual loop overheat leak detection in the pressure bulkhead

For dimensions refer to Fig. A-GBMAA Sheet 01

1 Drill the additional sensing element hole into the pressure bulkhead Frame

80/82 with a diameter of 13.5mm (0.53in.)

(30) Subtask 364033-831-207-002 - Install the sensing elements in the AFT and Bulk

cargo compartments

Work Zones and Access Panels

Zone Access/Work location

From 160 Work location Frame 55

To 310 Work location Frame 83

Manpower Resources

Manhours 11.25

Minimum number of person 1

Subtask elapsed time 11.25

Skills ELECTRICAL

Material necessary to do the job

Kit 364033D11R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

57 D3627006026600 1 PLACARD

355 NSA5549-00 1 CONNECTR

356 F3627011520400 1 PLACARD

357 NSA5543-00 22 CLAMP

358 35587-2-255 2 SNSGELEM

389 F3627011520000 1 PLACARD

562 35602-2-255 2 ELEMENT

563 35600-2-255 2 SNSGELEM

564 35586-2-255 2 ELEMENT

566 35594-2-255 2 SNSGELEM

570 35604-2-255 2 SNSGELEM

572 35597-2-255 1 SNSGELEM

574 35599-3-255 1 ELEMENT

591 F3627011520600 1 PLACARD

592 NSA5546-00 7 ANGLE

593 F3627011522200 1 PLACARD

594 F3627011520800 2 PLACARD

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 259

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@A340

SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

596 A2117050220000 1 RING

597 NAS1149C0832R 1 WASHER

602 NSA5539S 176 SLEEVE

604 NAS1149C0863R 1 WASHER

606 F3627011520200 2 PLACARD

607 NAS1919C04S02U 14 RIVET

609 NSA5527-03-01 1 SPACER

610 NSA5538-00 2 CLAMP

611 F3627011521000 1 PLACARD

612 NSA5542-00 6 NUT

805 NAS1802-3-13 1 SCREW

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Lockwire 0.6 Mm 19-018 As required

References

Aircraft Maintenance Manual (AMM) Task 36-22-17-400-801

Fig. A-GBGAB

Installation of the Sensing Elements in

the Bulk and AFT Cargo Compartments

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

Sheet 09

Fig. A-GBNAA

Tolerances for the Waviness and Bend

in the Electrical Wiring

Sheet 01

Sheet 02

(a) Install the sensing elements in the AFT and Bulk cargo compartments

Refer to AMM Task 36-22-17-400-801

1 For the installation of the sensing elements install the connection flanges

Refer to Fig. A-GBGAB Sheet 01 thru Fig. A-GBGAB Sheet 08

Put the angles, Item 592, in position within the given tolerance area, transfer

drill the rivet holes to the duct-brackets with the diameter between 3.28 mm

and 3.35 mm (0.129 in and 0.132 in) and install:

7 Angle NSA5546-00 Item 592

with:

14 Rivet-Blind NAS1919C04S02U Item 607

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 260

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SERVICE BULLETIN

2 Install the sensing elements between Frame 55 thru Frame 83

Refer to Fig. A-GBGAB Sheet 01 thru Fig. A-GBGAB Sheet 08

For the tolerances for waviness and bend in wires, refer to Fig. A-GBNAA

Sheet 01 thru Fig. A-GBNAA Sheet 02.

NOTE: The length compensation of the sensing elements must be

done at the couplings or retainer rings.

NOTE: The sensing elements must be installed in front of the

ventilation holes.

Install:

2 Sensing Element 35587-2-255 Item 358

2 Sensing Element 35602-2-255 Item 562

2 Sensing Element 35600-2-255 Item 563

2 Sensing Element 35586-2-255 Item 564

2 Sensing Element 35594-2-255 Item 566

2 Sensing Element 35604-2-255 Item 570

1 Sensing Element 35597-2-255 Item 572

1 Sensing Element 35599-3-255 Item 574

with:

1 Connector NSA5549-00 Item 355

22 Clamp NSA5543-00 Item 357

16 Clip Nut Item (399) Retained at

removal

6 Screw Item (408) Retained at

removal

1 Ring-Sealing A2117050220000 Item 596

1 Washer NAS1149C0832R Item 597

16 Screw Item (601) Retained at

removal

176 Sleeve-Protective NSA5539S Item 602

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 261

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@A340

SERVICE BULLETIN

1 Washer NAS1149C0863R Item 604

1 Spacer NSA5527-03-01 Item 609

2 Clamp NSA5538-00 Item 610

6 Nut NSA5542-00 Item 612

6 Nut Item (599) Retained at

removal

1 Screw NAS1802-3-13 Item 805

NOTE: Secure the nuts, Item 612/(599), with lockwire:

Lockwire 0.6 Mm 19-018 As required

3 Install the identification placards of the sensing-elements between Frame 55

thru Frame 83

Refer to Fig. A-GBGAB Sheet 01 thru Fig. A-GBGAB Sheet 07

Install:

1 Placard F3627011520400 Item 356

1 Placard F3627011520000 Item 389

1 Placard F3627011520600 Item 591

2 Placard F3627011520800 Item 594

1 Placard F3627011522200 Item 593

1 Placard F3627011521000 Item 611

2 Placard F3627011520200 Item 606

1 Placard D3627006026600 Item 57

(31) Subtask 364033-410-003-001 - If removed, install the ducts between FR39 and

FR40.

Work Zones and Access Panels

Zone Access/Work location

190

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 262

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@A340

SERVICE BULLETIN

Manpower Resources

Manhours 2.00

Minimum number of person 1

Subtask elapsed time 2.00

Skills AIRFRAME

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801

Fig. A-FBPAA

Removal/Installation of the Ducts

Between FR39 and FR40 for Access

Sheet 01

(a) Install :

Fig. A-FBPAA

(Refer to AMM Task 21-20-00-410-801)

1 Duct assy Item (125) Retained at

removal

1 Duct assy Item (126) Retained at

removal

1 Duct assy Item (127) Retained at

removal

(32) Subtask 364033-831-208-001 - Remove the sensing elements in the rear fuselage

Work Zones and Access Panels

Zone Access/Work location

310 Work location from Frame 80 to Frame 95

Manpower Resources

Manhours 2.75

Minimum number of person 1

Subtask elapsed time 2.75

Skills ELECTRICAL

References

Fig. A-GBHAA

Removal of the Sensing Elements in the

Rear Fuselage Section

Sheet 01

Sheet 02

Sheet 03

Sheet 04

(a) Remove the sensing elements in the rear fuselage

1 Remove the sensing elements between Frame 80/82 thru Frame 95

Refer to Fig. A-GBHAA Sheet 01 thru Fig. A-GBHAA Sheet 04

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 263

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SERVICE BULLETIN

Remove:

FIN 33HF

1 Sensing Element 35660-2-310 Item (371) Discard

FIN 34HF

1 Sensing Element 35301-75 Item (361) Discard

FIN 139HF

1 Sensing Element 35558-2-310 Item (364) Discard

FIN 140HF

1 Sensing Element 35636-2-310 Item (366) Discard

attached with:

3 Screw Item (601) Discard

35 Screw Item (601) Retain

39 Sleeve Item (602) Discard

6 Screw Item (620) Retain

6 Spacer Item (609) Retain

38 Clamp Item (610) Discard

37 Nut-Clip Item (399) Retain

1 Nut-Clip Item (399) Discard

3 Flange Item (59) Discard

3 Nut Item (612) Retain

2 Clamp Item (621) Retain

2 Remove the connector of the sensing element at Frame 80/82

Refer to Fig. A-GBHAA Sheet 01 thru Fig. A-GBHAA Sheet 04

Remove:

1 Connector Item (355) Discard

1 Washer Item (596) Discard

1 Washer Item (604) Discard

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 264

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@A340

SERVICE BULLETIN

(33) Subtask 364033-831-209-001 - Install the sensing elements in the rear fuselage

Manpower Resources

Manhours 5.75

Minimum number of person 1

Subtask elapsed time 5.75

Skills ELECTRICAL

Material necessary to do the job

Kit 364033D13R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

59 NSA5545-00 3 ANGLE

313 NAS1801-3-19 2 SCREW

355 NSA5549-00 1 CONNECTR

357 NSA5543-00 40 CLAMP

360 35301-74 1 CABLE

361 35301-75 1 CABLE

364 35566-2-310 2 ELEMENT

366 35624-2-310 2 ELEMENT

371 35661-2-310 1 ELEMENT

372 AS21919WCH04 12 CLAMP

373 AS21919WCH10 2 CLAMP

374 F3617052620200 1 PLACARD

392 F3627011521400 1 PLACARD

393 F3627011521600 2 PLACARD

394 F3627011521800 2 PLACARD

398 35659-3-310 1 ELEMENT

405 NSA935401-04 2 TIE

416 NAS1801-3-9 5 SCREW

496 NSA5527-03-08D 2 SPACER

591 F3617052620000 1 PLACARD

596 A2117050220000 1 RING

597 NAS1149C0832R 1 WASHER

602 NSA5539S 104 SLEEVE

604 NAS1149C0863R 1 WASHER

607 NAS1919C04S02U 6 RIVET

608 D3627006026800 1 PLACARD

609 NSA5527-03-01 4 SPACER

610 NSA5538-00 4 CLAMP

612 NSA5542-00 3 NUT

640 MS21042-3 5 NUT

682 NAS1149D0332K 7 WASHER

805 NAS1802-3-13 2 SCREW

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 265

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SERVICE BULLETIN

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Lockwire 0.6 Mm 19-018 As required

References

Fig. A-GBJAA

Installation of the Sensing Elements in

the Rear Fuselage Section

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

(a) Install the sensing elements in the rear fuselage

1 For the installation of the sensing elements install the connection flanges

Refer to Fig. A-GBJAA Sheet 01 thru Fig. A-GBJAA Sheet 08

Install:

3 Connection Flanges NSA5545-00 Item 59

with:

6 Rivet-Blind NAS1919C04S02U Item 607

2 Install the sensing elements between Frame 80/82 thru Frame 95

Refer to Fig. A-GBJAA Sheet 01 thru Fig. A-GBJAA Sheet 08

NOTE: The length compensation of the sensing elements must be

done at the couplings or retainer rings.

NOTE: The sensing elements must be installed in front of the

ventilation holes.

Install:

FIN 359HF

1 Sensing Element 35566-2-310 Item 364

FIN 139HF

1 Sensing Element 35566-2-310 Item 364

FIN 361HF

1 Cable-Electrical

Interconnecting

35301-74 Item 360

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 266

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@A340

SERVICE BULLETIN

FIN 34HF

1 Cable-Electrical

Interconnecting

35301-75 Item 361

FIN 360HF

1 Sensing Element 35624-2-310 Item 366

FIN 140HF

1 Sensing Element 35624-2-310 Item 366

FIN 358HF

1 Sensing Element 35659-3-310 Item 398

FIN 33HF

1 Sensing Element 35661-2-310 Item 371

with:

1 Connector NSA5549-00 Item 355

1 Washer NAS1149C0832R Item 597

1 Ring-Sealing A2117050220000 Item 596

1 Washer NAS1149C0863R Item 604

attached with:

37 Nut-Clip Item (399) Retained at

removal

35 Screw Item (601) Retained at

removal

6 Spacer Item (609) Retained at

removal

3 Nut Item (612) Retained at

removal

6 Screw Item (620) Retained at

removal

2 Clamp Item (621) Retained at

removal

2 Screw NAS1801-3-19 Item 313

40 Clamp NSA5543-00 Item 357

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 267

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@A340

SERVICE BULLETIN

12 Clamp AS21919WCH04 Item 372

2 Clamp AS21919WCH10 Item 373

5 Screw NAS1801-3-9 Item 416

2 Spacer NSA5527-03-08D Item 496

104 Sleeve-Protective NSA5539S Item 602

4 Spacer NSA5527-03-01 Item 609

4 Clamp NSA5538-00 Item 610

3 Nut NSA5542-00 Item 612

5 Nut MS21042-3 Item 640

7 Washer NAS1149D0332K Item 682

2 Screw NAS1802-3-13 Item 805

NOTE: Secure the nuts, Item 612/(612), with lockwire:

Lockwire 0.6 Mm 19-018 As required

3 Install the identification placards of the sensing-elements between Frame

80/82 thru Frame 95

Refer to Fig. A-GBJAA Sheet 01 thru Fig. A-GBJAA Sheet 08

Install:

1 Placard F3617052620200 Item 374

1 Placard F3627011521400 Item 392

2 Placard F3627011521600 Item 393

2 Placard F3627011521800 Item 394

2 Tie-Cable NSA935401-04 Item 405

1 Placard F3617052620000 Item 591

1 Placard D3627006026800 Item 608

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 268

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@A340

SERVICE BULLETIN

(34) Subtask 364033-831-210-001 - Install the sleeves at the APU Bleed Air Duct

Work Zones and Access Panels

Zone Access/Work location

310 Work location from Frame 80 to Frame 95

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills ELECTRICAL

Material necessary to do the job

Kit 364033D16R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

375 F3617062400000 1 SLEEVE

376 F3617062400200 1 SLEEVE

377 F3617062400400 1 SLEEVE

378 F3617062400600 1 SLEEVE

379 F3617062400800 1 SLEEVE

380 F3617062401000 1 SLEEVE

381 F3617062401200 1 SLEEVE

382 F3617062401400 1 SLEEVE

384 F3617062401800 1 SLEEVE

References

Fig. A-GBKAA

Installation of the Sleeves at the APU

Bleed Air Duct

Sheet 01

(a) Install the sleeves at the APU Bleed Air Duct between Frame 80/82 thru Frame 95

Refer to Fig. A-GBKAA Sheet 01

install the sleeves:

1 Sleeve Assy F3617062400000 Item 375

1 Sleeve Assy F3617062400200 Item 376

1 Sleeve Assy F3617062400400 Item 377

1 Sleeve Assy F3617062400600 Item 378

1 Sleeve Assy F3617062400800 Item 379

1 Sleeve Assy F3617062401000 Item 380

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 269

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@A340

SERVICE BULLETIN

1 Sleeve Assy F3617062401200 Item 381

1 Sleeve Assy F3617062401400 Item 382

1 Sleeve Assy F3617062401800 Item 384

NOTE: Make sure that the blowout apertures of the blankets are close to

(under) the sensing elements.

**CONF 003

(1) Subtask 364033-831-016-001 - Modify the Wiring between the Avionics

Compartment and the Cargo Compartment.

Work Zones and Access Panels

Zone Access/Work location

190

Manpower Resources

Manhours 2.00

Minimum number of person 2

Subtask elapsed time 2.00

Skills ELECTRICAL

Material necessary to do the job

Kit 364033A02R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

169 NSA935401-03 300 TIE

F9000095227895 BUNDLE

NSA935401-08 300 TIE

NSA935401-13 300 TIE

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 270

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SERVICE BULLETIN

References

Fig. A-FBMAA

Installation of the New Harness 2SG

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

Sheet 09

Sheet 10

Sheet 11

Sheet 12

Sheet 13

Sheet 14

Sheet 15

Sheet 16

Sheet 17

Sheet 18

Sheet 19

Sheet 20

Sheet 21

Sheet 22

Fig. A-FCBAA

Modification of the Wiring between the

Cargo Compartment and the Avionics

Compartment

Sheet 01

Sheet 02

(a) As shown in Fig. A-FBMAA Sheet 01, install the wire, using spares conduits

between Frame 37 and Frame 53.2, as shown on the wiring diagram, Fig. AFCBAA Sheet 01 and as given in the Hook-up Chart line :

- 1 (Refer to Fig. A-FCBAA Sheet 02) supplied in :

Bundle F9000095227895

NOTE: The spares conduits is divided in two parts. The first parts go away

from Frame 40 to Frame 47 and the second parts go away from

Frame 48 to Frame 53.2

(b) Attach the wires with :

300 Tie-Cable NSA935401-03 Item 169

300 Tie-Cable NSA935401-08

300 Tie-Cable NSA935401-13

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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@A340

SERVICE BULLETIN

(2) Subtask 364033-831-017-001 - Modify the Wiring in the Main rack 800VU.

Work Zones and Access Panels

Zone Access/Work location

120 Work location Electrical panel 800VU

Manpower Resources

Manhours 4.00

Minimum number of person 2

Subtask elapsed time 2.00

Skills ELECTRICAL

Material necessary to do the job

Kit 364033A02R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

169 NSA935401-03 50 TIE

F9000095227895 BUNDLE

NSA935401-06 50 TIE

NSA935401-13 50 TIE

References

Aircraft Maintenance Manual (AMM) Task 36-11-34-000-802

Task 36-11-34-400-802

Fig. A-FCAAA

Modification of the Wiring in the Main

Rack 800VU

Sheet 01

Sheet 02

Sheet 03

Sheet 04

(a) Remove and retain the BMC (FIN 1HA1, 1HA2, 1HA3 and 1HA4) (Refer to AMM

Task 36-11-34-000-802).

(b) Remove the wires as shown on the wiring diagram Fig. A-FCAAA Sheet 01, and as

given in the Hook-up Chart lines :

- 1 thru 5 (Refer to Fig. A-FCAAA Sheet 04).

(c) Install the wires as shown on the wiring diagrams, Fig. A-FCAAA Sheet 02 and Fig.

A-FCAAA Sheet 03 and as given in the Hook-up Chart lines :

- 9 thru 19 (Refer to Fig. A-FCAAA Sheet 04) supplied in :

Bundle F9000095227895

(d) Attach the wires with :

50 Tie-Cable NSA935401-03 Item 169

50 Tie-Cable NSA935401-06

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 272

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SERVICE BULLETIN

50 Tie-Cable NSA935401-13

(e) Install the BMC (FIN 1HA1, 1HA2, 1HA3 and 1HA4) (Refer to AMM Task

36-11-34-400-802).

(3) Subtask 364033-831-001-001 - Remove the sensing elements and the supports

between FR39 and FR44.

Work Zones and Access Panels

Zone Access/Work location

190 Work location from Frame 39 to Frame 44

Manpower Resources

Manhours 4.00

Minimum number of person 1

Subtask elapsed time 4.00

Skills AIRFRAME

References

Aircraft Maintenance Manual (AMM) Task 36-22-17-000-801

Task 36-22-17-000-802

Fig. A-FBAAA

Removal of the Sensing Elements

between FR39 and FR55 on the LH side

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

(a) Remove :

Fig. A-FBAAA Sheet 01 Fig. A-FBAAA Sheet 02

(Refer to AMM Task 36-22-17-000-801 and AMM Task 36-22-17-000-802)

22 Screw Item (20) Discard

32 Washer Item (14) Discard

32 Clamp Item (86) Discard

32 Sleeve Item (13) Discard

5 Screw Item (91) Discard

10 Spacer Item (16) Discard

5 Screw Item (21) Discard

2 Nut Item (15) Discard

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 273

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@A340

SERVICE BULLETIN

FIN 97HF

1 Sensing Element 35610-2-255 Item (1) Discard

FIN 98HF

1 Sensing Element 35624-2-255 Item (2) Discard

4 Rivet Item (11) Discard

2 Support Item (10) Discard

(4) Subtask 364033-831-002-001 - Remove the sensing elements and the supports

between FR44 and FR51.

Work Zones and Access Panels

Zone Access/Work location

190 Work location from Frame 44 to Frame 51

Manpower Resources

Manhours 4.00

Minimum number of person 1

Subtask elapsed time 4.00

Skills AIRFRAME

References

Aircraft Maintenance Manual (AMM) Task 36-22-17-000-801

Fig. A-FBAAA

Removal of the Sensing Elements

between FR39 and FR55 on the LH side

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

(a) Remove :

Fig. A-FBAAA Sheet 01 Fig. A-FBAAA Sheet 03

(Refer to AMM Task 36-22-17-000-801)

18 Screw Item (21) Discard

30 Washer Item (14) Discard

30 Clamp Item (86) Discard

30 Sleeve Item (13) Discard

18 Spacer Item (16) Discard

12 Screw Item (20) Discard

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 274

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@A340

SERVICE BULLETIN

2 Nut Item (15) Discard

FIN 99HF

1 Sensing Element 35612-2-255 Item (3) Discard

FIN 100HF

1 Sensing Element 35605-2-255 Item (6) Discard

4 Rivet Item (11) Discard

2 Support Item (10) Discard

(5) Subtask 364033-831-003-001 - Remove the sensing elements and the supports

between FR51 and FR53.6.

Work Zones and Access Panels

Zone Access/Work location

190 Work location from Frame 51 to Frame 53.6

Manpower Resources

Manhours 4.00

Minimum number of person 1

Subtask elapsed time 4.00

Skills AIRFRAME

References

Aircraft Maintenance Manual (AMM) Task 36-22-17-000-801

Task 36-22-17-000-802

Fig. A-FBAAA

Removal of the Sensing Elements

between FR39 and FR55 on the LH side

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

(a) Remove :

Fig. A-FBAAA Sheet 01 Fig. A-FBAAA Sheet 04

(Refer to AMM Task 36-22-17-000-801 and AMM Task 36-22-17-000-802)

18 Screw Item (21) Discard

37 Washer Item (14) Discard

37 Clamp Item (86) Discard

37 Sleeve Item (13) Discard

23 Spacer Item (16) Discard

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 275

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@A340

SERVICE BULLETIN

16 Screw Item (20) Discard

1 Screw Item (93) Discard

1 Spacer Item (18) Discard

2 Screw Item (91) Discard

3 Nut Item (15) Discard

FIN 101HF

1 Sensing Element 35603-2-255 Item (4) Discard

FIN 102HF

1 Sensing Element 35600-2-255 Item (5) Discard

FIN 23HF

1 Sensing Element 35571-2-255 Item (7) Discard

6 Rivet Item (11) Discard

3 Support Item (10) Discard

(6) Subtask 364033-831-004-001 - Remove the sensing elements and the supports

between FR53.6 and FR55.

Work Zones and Access Panels

Zone Access/Work location

190 Work location from Frame 53.6 to Frame 55

Manpower Resources

Manhours 4.00

Minimum number of person 1

Subtask elapsed time 4.00

Skills AIRFRAME

References

Aircraft Maintenance Manual (AMM) Task 36-22-17-000-801

Fig. A-FBAAA

Removal of the Sensing Elements

between FR39 and FR55 on the LH side

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

(a) Remove :

Fig. A-FBAAA Sheet 01 Fig. A-FBAAA Sheet 05

(Refer to AMM Task 36-22-17-000-801)

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 276

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@A340

SERVICE BULLETIN

19 Screw Item (20) Discard

27 Washer Item (14) Discard

27 Clamp Item (86) Discard

27 Sleeve Item (13) Discard

4 Screw Item (91) Discard

12 Spacer Item (16) Discard

4 Screw Item (21) Discard

2 Nut Item (15) Discard

FIN 24HF

1 Sensing Element 35580-2-255 Item (8) Discard

FIN 25HF

1 Sensing Element 35611-3-255 Item (9) Discard

2 Rivet Item (11) Discard

1 Support Item (10) Discard

(7) Subtask 364033-010-002-001 - If necessary, remove the ducts between FR53.5 and

FR53.6 for access.

Work Zones and Access Panels

Zone Access/Work location

150 Work location from Frame 53.5 to Frame 53.6

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills AIRFRAME

References

Aircraft Maintenance Manual (AMM) Task 36-12-41-000-801

Fig. A-FBBAA

Removal/Installation of the Ducts

between FR53.6 and FR53.7 on the LH

side (for Access)

Sheet 01

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 277

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SERVICE BULLETIN

(a) Remove :

Fig. A-FBBAA

(Refer to AMM Task 36-12-41-000-801)

1 Duct assy Item (112) Retain

1 Duct assy Item (112) Retain

1 Duct assy Item (114) Retain

(8) Subtask 364033-831-005-001 - Drill a new hole in the structure between FR53.5 and

FR53.6.

Work Zones and Access Panels

Zone Access/Work location

150 Work location from Frame 53.5 to Frame 53.6

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills AIRFRAME

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Chemical Conversion

Coating Yellow Aluminum

13-002 As required

Anti-Corrosion Primer

(polyurethane)

16-001 As required

Polyurethane Finnish Paint 16-018 As required

References

Fig. A-FBCAA

Drilling of a New Hole in the Structure

between FR53.5 and FR53.6 on the LH

side and Installation of Sensing

Elements

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

(a) Drill one hole on the structure between FR53.5 and FR53.6 to a diameter

comprised between 13.5mm (0.531in.) Min. and 13.7mm (0.539 in.) Max. as shown

on Fig. A-FBCAA.

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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SERVICE BULLETIN

(b) Do a spotfacing on the structure between FR53.5 and 53.6 to a diameter of 24mm

(0.944 in.) with a radius of 2mm (0.078in.)

NOTE: Be careful at the depth : 2mm (0.078 in.) Min. and 3mm (0.118 in.)

Max.

(c) Protect the hole and the spotfacing with :

Chemical

Conversion Coating

Yellow Aluminum

13-002 As required

Anti-Corrosion

Primer

(polyurethane)

16-001 As required

Polyurethane

Finnish Paint

16-018 As required

(9) Subtask 364033-831-006-001 - Install a new support for the routing of the sensing

elements between FR53.5 and FR53.6.

Work Zones and Access Panels

Zone Access/Work location

150 Work location from Frame 53.5 to Frame 53.6

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills NON SPECIFIC

Material necessary to do the job

Kit 364033A01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

96 F5392059300000 1 SUPPORT

97 ASNA2050DCJ3215 2 RIVET

Reidentified part set REIDA01

ITEM NEW PART N ̊ KEYWORD ITEM OLD PART N ̊ SEE

NOTES

F0041196200000 BLANKET F2581571700000

F2582261900000

F0041196300000 BLANKET F2581566600000

F0041196400000 BLANKET F2581666600000

F0041196500000 BLANKET F2581677800000

F0041196600000 BLANKET F2581677900000

F0041196700000 BLANKET F2582242300000

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 279

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SERVICE BULLETIN

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Adhesive Tape (insulation

Blanket Repair)

08-073 As required

Interfay Sealant 09-005A As required

Corrosion Inhibiting Fillet

Consistency

09-016B As required

References

Fig. A-FBFAA

Installation of a New Bracket between

FR53.5 and FR53.6

Sheet 01

Sheet 02

(a) Move the insulation blanket to get access to the modification area.

(b) Put the bracket Item 96 in position as shown on Fig. A-FBFAA.

(c) Drill two holes on the structure to a diameter comprised between 3.25mm (0.128in.)

and 3.35mm (0.132in.) to match the holes of the bracket Item 96.

Fig. A-FBFAA

(d) Cut the insulation blanket to permit the installation of the bracket Item 96.

NOTE: For the repair of the insulation blanket use :

Adhesive Tape

(insulation Blanket

Repair)

08-073 As required

(e) Re-identify the insulation blanket :

1 Blanket-Insulation F2581571700000

or

1 Blanket-Insulation F2582261900000

becomes

1 Blanket-Insulation F0041196200000

or

1 Blanket-Insulation F2581566600000

becomes

1 Blanket-Insulation F0041196300000

or

1 Blanket-Insulation F2581666600000

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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SERVICE BULLETIN

becomes

1 Blanket-Insulation F0041196400000

or

1 Blanket-Insulation F2581677800000

becomes

1 Blanket-Insulation F0041196500000

or

1 Blanket-Insulation F2581677900000

becomes

1 Blanket-Insulation F0041196600000

or

1 Blanket-Insulation F2582242300000

becomes

1 Blanket-Insulation F0041196700000

(f) Install :

Fig. A-FBFAA

1 Support F5392059300000 Item 96

2 Rivet ASNA2050DCJ3215 Item 97

NOTE: To the interface of the new bracket and the structure, apply :

Interfay Sealant 09-005A As required

NOTE: Do a sealant bead around new parts with :

Corrosion Inhibiting

Fillet Consistency

09-016B As required

NOTE: Wet install the fasteners with :

Interfay Sealant 09-005A As required

(g) Install the insulation blanket.

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 281

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SERVICE BULLETIN

(10) Subtask 364033-410-001-001 - If removed, install the ducts between FR53.5 and

FR53.6.

Work Zones and Access Panels

Zone Access/Work location

150 Work location from Frame 53.5 to Frame 53.6

Manpower Resources

Manhours 2.00

Minimum number of person 1

Subtask elapsed time 2.00

Skills AIRFRAME

References

Aircraft Maintenance Manual (AMM) Task 36-12-41-400-801

Fig. A-FBBAA

Removal/Installation of the Ducts

between FR53.6 and FR53.7 on the LH

side (for Access)

Sheet 01

(a) Install :

(Refer to AMM Task 36-12-41-400-801)

1 Duct assy Item (112) Retained at

removal

1 Duct assy Item (112) Retained at

removal

1 Duct assy Item (114) Retained at

removal

(11) Subtask 364033-010-003-001 - If necessary, remove the ducts between FR43 and

FR45 for access.

Work Zones and Access Panels

Zone Access/Work location

190 Work location from Frame 43 to Frame 45

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 36-12-41-000-801

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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References

Fig. A-FBDAA

Removal/Installation of the Ducts

between FR44 and FR47 on the LH side

(for Access)

Sheet 01

(a) Remove :

(Refer to AMM Task 36-12-41-000-801)

1 Duct assy Item (115) Retain

1 Duct assy Item (116) Retain

(12) Subtask 364033-831-007-001 - Replace the web assy and the half clamp assy at

FR44.

Work Zones and Access Panels

Zone Access/Work location

190 Work location Frame 44

Manpower Resources

Manhours 3.00

Minimum number of person 1

Subtask elapsed time 3.00

Skills AIRFRAME

Material necessary to do the job

Kit 364033A01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

117 F5331591000200 1 WEB

118 F5331583500200 1 CLAMP

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Corrosion Inhibiting Fillet

Consistency

09-016B As required

Low Adhesion Polysulfide

Sealant

09-019B As required

References

Fig. A-FBEAA

Replacement of the Web Assy at FR44

on the LH side

Sheet 01

Sheet 02

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 283

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SERVICE BULLETIN

(a) Remove :

Fig. A-FBEAA

17 Screw Item (119) Retain

17 Washer Item (124) Retain

1 Strip cover assy Item (122) Retain

2 Screw Item (120) Retain

1 Half clamp assy F5331583500000 Item (118) Discard

1 Half clamp assy Item (121) Retain

1 Bracket Item (123) Retain

1 Web Assy F5331591000000 Item (117) Discard

NOTE: It is not necessary to remove completely the bracket Item (123).

(b) Install :

Fig. A-FBEAA

1 Web Assy F5331591000200 Item 117

1 Bracket Item (123) Retained at

removal

1 Half clamp assy Item (121) Retained at

removal

1 Half clamp assy F5331583500200 Item 118

2 Screw Item (120) Retained at

removal

1 Strip cover assy Item (122) Retained at

removal

17 Washer Item (124) Retained at

removal

17 Screw Item (119) Retained at

removal

NOTE: Install the new web assy with :

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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SERVICE BULLETIN

Corrosion Inhibiting

Fillet Consistency

09-016B As required

and

Low Adhesion

Polysulfide Sealant

09-019B As required

(13) Subtask 364033-831-008-001 - Install the new brackets for the routing of the

sensing elements at FR44.

Work Zones and Access Panels

Zone Access/Work location

190 Work location Frame 44

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills AIRFRAME

Material necessary to do the job

Kit 364033A01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

97 ASNA2050DCJ3215 2 RIVET

98 F0041178800000 1 SUPPORT

99 F0041178800100 1 SUPPORT

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Interfay Sealant 09-005A As required

Corrosion Inhibiting Fillet

Consistency

09-016B As required

References

Fig. A-FBGAA

Installation of Two New Brackets at

FR44

Sheet 01

Sheet 02

(a) Put the brackets Item 98 and 99 in position as shown on Fig. A-FBGAA.

(b) Drill two holes to a diameter comprised between 3.25mm (0.128in.) and 3.35mm

(0.132in.) as shown on Fig. A-FBGAA.

(c) Install :

1 Support F0041178800000 Item 98

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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SERVICE BULLETIN

1 Support F0041178800100 Item 99

2 Rivet ASNA2050DCJ3215 Item 97

NOTE: To the interface of the new bracket and the structure apply :

Interfay Sealant 09-005A As required

NOTE: Do a sealant bead around new parts with :

Corrosion Inhibiting

Fillet Consistency

09-016B As required

NOTE: Wet install the fasteners with :

Interfay Sealant 09-005A As required

(14) Subtask 364033-410-002-001 - If removed, install the ducts between FR43 and

FR45.

Work Zones and Access Panels

Zone Access/Work location

190 Work location from Frame 43 to Frame 45

Manpower Resources

Manhours 2.00

Minimum number of person 1

Subtask elapsed time 2.00

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 36-12-41-400-801

Fig. A-FBDAA

Removal/Installation of the Ducts

between FR44 and FR47 on the LH side

(for Access)

Sheet 01

(a) Install :

(Refer to AMM Task 36-12-41-400-801)

1 Duct assy Item (115) Retained at

removal

1 Duct assy Item (116) Retained at

removal

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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SERVICE BULLETIN

(15) Subtask 364033-831-009-001 - Install the sensing elements and the supports

between FR39 and FR44.

Work Zones and Access Panels

Zone Access/Work location

190 Work location from Frame 39 to Frame 44

Manpower Resources

Manhours 14.00

Minimum number of person 1

Subtask elapsed time 14.00

Skills AIRFRAME

Material necessary to do the job

Kit 364033A01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

10 NSA5543-00 30 CLAMP

11 ASNA0342T04-01 4 BOLT

13 NSA5539S 62 SLEEVE

14 ASNA2397-10L 34 WASHER

15 NSA5542-00 4 NUT

16 NSA5527-03-01 8 SPACER

18 NSA5527-03-11 6 SPACER

20 NAS6603-1 19 BOLT

21 NAS6603-9 8 BOLT

24 NAS6603-15 6 BOLT

29 NAS6603-2 2 BOLT

30 NSA5546-00 2 ANGLE

32 F1131031621700 2 PLACARD

33 F1131031623700 2 PLACARD

34 F1131031621800 1 PLACARD

35 F1131031623800 1 PLACARD

70 F3611548300000 1 SUPPORT

71 F3611548800000 1 SUPPORT

78 F3611549700000 1 SUPPORT

79 F3611549100000 1 SUPPORT

100 35606-2-255 1 SNSGELEM

101 35621-2-255 1 SNSGELEM

102 35620-2-255 1 SNSGELEM

113 35610-2-255 1 SNSGELEM

References

Fig. A-FBHAA

Installation of the New Sensing

Elements between FR39 and FR44 on

LH side

Sheet 01

Sheet 02

Sheet 03

Sheet 04

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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SERVICE BULLETIN

(a) Install the sensing elements and the supports between FR39 and FR40.2.

1 Install the supports between FR39 and FR40 :

1 Angle NSA5546-00 Item 30

2 Rivet-Blind ASNA0342T04-01 Item 11

8 Clamp NSA5543-00 Item 10

6 Spacer NSA5527-03-01 Item 16

2 Spacer NSA5527-03-11 Item 18

8 Washer ASNA2397-10L Item 14

6 Bolt NAS6603-9 Item 21

2 Bolt NAS6603-15 Item 24

2 Install the supports between FR40 and FR40.2 :

1 Support F3611549100000 Item 79

1 Support F3611549700000 Item 78

5 Clamp NSA5543-00 Item 10

1 Spacer NSA5527-03-01 Item 16

8 Washer ASNA2397-10L Item 14

1 Bolt NAS6603-9 Item 21

6 Bolt NAS6603-1 Item 20

2 Bolt NAS6603-2 Item 29

1 Angle NSA5546-00 Item 30

2 Rivet-Blind ASNA0342T04-01 Item 11

3 Install the placards between FR39 and FR40.2 :

2 Placard F1131031621700 Item 32

2 Placard F1131031623700 Item 33

1 Placard F1131031621800 Item 34

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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SERVICE BULLETIN

1 Placard F1131031623800 Item 35

4 Install the sensing elements between FR39 and FR40.2 :

FIN 97HF

1 Sensing Element 35606-2-255 Item 100

FIN 302HF

1 Sensing Element 35610-2-255 Item 113

28 Sleeve-Protective NSA5539S Item 13

4 Nut NSA5542-00 Item 15

NOTE: Secure the nuts Item 15 with wire-lock MS20995C32 Item 27.

(b) Install the sensing elements and the supports between FR40.2 and FR44.

1 Install the supports between FR40.2 and FR44 :

1 Support F3611548300000 Item 70

1 Support F3611548800000 Item 71

17 Clamp NSA5543-00 Item 10

4 Spacer NSA5527-03-11 Item 18

1 Spacer NSA5527-03-01 Item 16

18 Washer ASNA2397-10L Item 14

13 Bolt NAS6603-1 Item 20

1 Bolt NAS6603-9 Item 21

4 Bolt NAS6603-15 Item 24

2 Install the sensing elements between FR40.2 and FR44 :

FIN 98HF

1 Sensing Element 35620-2-255 Item 102

FIN 303HF

1 Sensing Element 35621-2-255 Item 101

34 Sleeve-Protective NSA5539S Item 13

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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(16) Subtask 364033-831-010-001 - Install the sensing elements and the supports

between FR44 and FR50.

Work Zones and Access Panels

Zone Access/Work location

190 Work location from Frame 44 to Frame 50

Manpower Resources

Manhours 14.00

Minimum number of person 1

Subtask elapsed time 14.00

Skills AIRFRAME

Material necessary to do the job

Kit 364033A01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

10 NSA5543-00 29 CLAMP

11 ASNA0342T04-01 4 BOLT

13 NSA5539S 58 SLEEVE

14 ASNA2397-10L 35 WASHER

15 NSA5542-00 8 NUT

16 NSA5527-03-01 11 SPACER

17 NSA5527-03-10 1 SPACER

18 NSA5527-03-11 3 SPACER

19 NAS6603-24 2 BOLT

20 NAS6603-1 14 BOLT

21 NAS6603-9 9 BOLT

23 NAS6603-16 1 BOLT

26 NAS6603-32 1 BOLT

29 NAS6603-2 8 BOLT

30 NSA5546-00 2 ANGLE

34 F1131031621800 1 PLACARD

35 F1131031623800 1 PLACARD

36 F1131031623900 2 PLACARD

37 F1131031621900 2 PLACARD

38 F1131031624000 2 PLACARD

39 F1131031622000 2 PLACARD

40 F1131031622100 1 PLACARD

41 F1131031624100 1 PLACARD

79 F3611549100000 4 SUPPORT

80 F3611549500000 1 SUPPORT

81 F3611549600000 1 SUPPORT

103 35618-2-255 2 SNSGELEM

105 35598-2-255 1 SNSGELEM

114 35597-2-255 1 SNSGELEM

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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SERVICE BULLETIN

References

Fig. A-FBJAA

Installation of the New Sensing

Elements between FR44 and FR50 on

LH side

Sheet 01

Sheet 02

Sheet 03

Sheet 04

(a) Install the sensing elements and the supports between FR44 and FR46.

1 Install the supports between FR44 and FR46 :

1 Support F3611549600000 Item 81

17 Clamp NSA5543-00 Item 10

9 Spacer NSA5527-03-01 Item 16

3 Spacer NSA5527-03-11 Item 18

21 Washer ASNA2397-10L Item 14

2 Bolt NAS6603-24 Item 19

5 Bolt NAS6603-1 Item 20

7 Bolt NAS6603-9 Item 21

1 Bolt NAS6603-16 Item 23

2 Bolt NAS6603-2 Item 29

2 Install the placards at FR44 :

1 Placard F1131031621800 Item 34

1 Placard F1131031623800 Item 35

1 Placard F1131031623900 Item 36

1 Placard F1131031621900 Item 37

3 Install the sensing elements between FR44 and FR46 :

FIN 99HF

1 Sensing Element 35618-2-255 Item 103

FIN 304HF

1 Sensing Element 35618-2-255 Item 103

34 Sleeve-Protective NSA5539S Item 13

4 Nut NSA5542-00 Item 15

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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(b) Install the sensing elements and the supports between FR46 and FR50.

1 Install the supports between FR46 and FR50 :

2 Angle NSA5546-00 Item 30

4 Rivet-Blind ASNA0342T04-01 Item 11

1 Support F3611549500000 Item 80

4 Support F3611549100000 Item 79

12 Clamp NSA5543-00 Item 10

2 Spacer NSA5527-03-01 Item 16

1 Spacer NSA5527-03-10 Item 17

14 Washer ASNA2397-10L Item 14

9 Bolt NAS6603-1 Item 20

2 Bolt NAS6603-9 Item 21

1 Bolt NAS6603-32 Item 26

6 Bolt NAS6603-2 Item 29

2 Install the placards between FR46 and FR50 :

1 Placard F1131031623900 Item 36

1 Placard F1131031621900 Item 37

2 Placard F1131031624000 Item 38

2 Placard F1131031622000 Item 39

1 Placard F1131031622100 Item 40

1 Placard F1131031624100 Item 41

3 Install the sensing elements between FR46 and FR50 :

FIN 100HF

1 Sensing Element 35597-2-255 Item 114

FIN 305HF

1 Sensing Element 35598-2-255 Item 105

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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24 Sleeve-Protective NSA5539S Item 13

4 Nut NSA5542-00 Item 15

NOTE: Secure the nuts Item 15 with wire-lock MS20995C32 Item 27.

(17) Subtask 364033-831-011-001 - Install the sensing elements and the supports

between FR50 and FR53.6.

Work Zones and Access Panels

Zone Access/Work location

190 Work location from Frame 50 to Frame 53.6

Manpower Resources

Manhours 21.00

Minimum number of person 1

Subtask elapsed time 21.00

Skills AIRFRAME

Material necessary to do the job

Kit 364033A01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

10 NSA5543-00 37 CLAMP

11 ASNA0342T04-01 6 BOLT

13 NSA5539S 74 SLEEVE

14 ASNA2397-10L 51 WASHER

15 NSA5542-00 6 NUT

16 NSA5527-03-01 16 SPACER

18 NSA5527-03-11 1 SPACER

20 NAS6603-1 23 BOLT

21 NAS6603-9 16 BOLT

22 NSA5527-03-15 1 SPACER

24 NAS6603-15 1 BOLT

25 NSA5545-00 1 ANGLE

28 NAS6603-12 1 BOLT

29 NAS6603-2 10 BOLT

30 NSA5546-00 2 ANGLE

40 F1131031622100 1 PLACARD

41 F1131031624100 1 PLACARD

42 F1131031622200 2 PLACARD

43 F1131031624200 2 PLACARD

44 F1131031620400 2 PLACARD

45 F1131031624300 2 PLACARD

70 F3611548300000 1 SUPPORT

72 F3611548700000 1 SUPPORT

73 F3611548500000 1 SUPPORT

74 F3611548900000 1 SUPPORT

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

75 F3611548400000 1 SUPPORT

76 F3611548200000 1 SUPPORT

77 F3611548620000 1 SUPPORT

79 F3611549100000 3 SUPPORT

82 F3611549400000 1 SUPPORT

83 F3611549800000 1 SUPPORT

84 F3611549300000 1 SUPPORT

104 35567-3-255 1 SNSGELEM

106 35595-2-255 3 SNSGELEM

107 35596-2-255 1 SNSGELEM

108 35568-4-255 1 SNSGELEM

References

Fig. A-FBKAA

Installation of the New Sensing

Elements between FR50 and FR53.6 on

LH side

Sheet 01

Sheet 02

Sheet 03

Sheet 04

(a) Install the sensing elements and the supports between FR50 and FR53.2.

1 Install the supports between FR50 and FR53.2 :

1 Support F3611548700000 Item 72

1 Support F3611548400000 Item 75

1 Support F3611549400000 Item 82

1 Angle NSA5546-00 Item 30

2 Rivet-Blind ASNA0342T04-01 Item 11

13 Clamp NSA5543-00 Item 10

7 Spacer NSA5527-03-01 Item 16

16 Washer ASNA2397-10L Item 14

9 Bolt NAS6603-1 Item 20

7 Bolt NAS6603-9 Item 21

2 Install the placards between FR50 and FR53.2 :

1 Placard F1131031622100 Item 40

1 Placard F1131031624100 Item 41

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1 Placard F1131031622200 Item 42

1 Placard F1131031624200 Item 43

3 Install the sensing elements between FR50 and FR53.2 :

FIN 101HF

1 Sensing Element 35595-2-255 Item 106

FIN 306HF

1 Sensing Element 35595-2-255 Item 106

26 Sleeve-Protective NSA5539S Item 13

2 Nut NSA5542-00 Item 15

NOTE: Secure the nuts Item 15 with wire-lock MS20995C32 Item 27.

(b) Install the sensing elements and the supports between FR53.2 and FR53.6.

1 Install the supports between FR53.2 and FR53.6 :

1 Support F3611548300000 Item 70

1 Support F3611548500000 Item 73

1 Support F3611548900000 Item 74

1 Support F3611548200000 Item 76

1 Support F3611548620000 Item 77

3 Support F3611549100000 Item 79

1 Support F3611549800000 Item 83

1 Support F3611549300000 Item 84

1 Angle NSA5545-00 Item 25

1 Angle NSA5546-00 Item 30

4 Rivet-Blind ASNA0342T04-01 Item 11

24 Clamp NSA5543-00 Item 10

9 Spacer NSA5527-03-01 Item 16

1 Spacer NSA5527-03-11 Item 18

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1 Spacer NSA5527-03-15 Item 22

35 Washer ASNA2397-10L Item 14

14 Bolt NAS6603-1 Item 20

9 Bolt NAS6603-9 Item 21

1 Bolt NAS6603-15 Item 24

1 Bolt NAS6603-12 Item 28

10 Bolt NAS6603-2 Item 29

2 Install the placards between FR53.2 and FR53.6 :

1 Placard F1131031622200 Item 42

1 Placard F1131031624200 Item 43

2 Placard F1131031620400 Item 44

2 Placard F1131031624300 Item 45

3 Install the sensing elements between FR53.2 and FR53.6 :

FIN 102HF

1 Sensing Element 35595-2-255 Item 106

FIN 307HF

1 Sensing Element 35596-2-255 Item 107

FIN 23HF

1 Sensing Element 35568-4-255 Item 108

FIN 308HF

1 Sensing Element 35567-3-255 Item 104

48 Sleeve-Protective NSA5539S Item 13

4 Nut NSA5542-00 Item 15

NOTE: Secure the nuts Item 15 with wire-lock MS20995C32 Item 27.

(18) Subtask 364033-831-012-001 - Install the sensing elements and the supports

between FR53.6 and FR55.

Work Zones and Access Panels

Zone Access/Work location

190 Work location from Frame 53.6 to Frame 55

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Manpower Resources

Manhours 14.00

Minimum number of person 1

Subtask elapsed time 14.00

Skills AIRFRAME

Material necessary to do the job

Kit 364033A01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

10 NSA5543-00 27 CLAMP

11 ASNA0342T04-01 2 BOLT

13 NSA5539S 55 SLEEVE

14 ASNA2397-10L 32 WASHER

15 NSA5542-00 2 NUT

16 NSA5527-03-01 6 SPACER

17 NSA5527-03-10 2 SPACER

18 NSA5527-03-11 5 SPACER

20 NAS6603-1 17 BOLT

21 NAS6603-9 1 BOLT

26 NAS6603-32 2 BOLT

29 NAS6603-2 2 BOLT

30 NSA5546-00 1 ANGLE

70 F3611548300000 1 SUPPORT

79 F3611549100000 1 SUPPORT

85 NSA5549-90 2 CONNECTR

86 NSA5538-00 3 CLAMP

87 NAS6603-17 5 BOLT

88 F1131031620500 1 PLACARD

89 F1131031624400 1 PLACARD

90 F1131031620600 1 PLACARD

91 F1131031624500 1 PLACARD

93 F3611549200095 1 SUPPORT

94 NAS6603-10 5 BOLT

95 F3611549000000 1 SUPPORT

109 35597-3-255 1 SNSGELEM

110 35587-2-255 1 SNSGELEM

111 35627-2-255 1 SNSGELEM

112 35625-2-255 1 SNSGELEM

References

Fig. A-FBLAA

Installation of the New Sensing

Elements between FR53.6 and FR55 on

LH side

Sheet 01

Sheet 02

Sheet 03

Sheet 04

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(a) Install the sensing elements and the supports between FR53.6 and FR55.

1 Install the supports between FR53.6 and FR55 :

1 Support F3611548300000 Item 70

1 Support F3611549100000 Item 79

1 Support F3611549200095 Item 93

1 Support F3611549000000 Item 95

1 Angle NSA5546-00 Item 30

2 Rivet-Blind ASNA0342T04-01 Item 11

27 Clamp NSA5543-00 Item 10

3 Clamp NSA5538-00 Item 86

6 Spacer NSA5527-03-01 Item 16

2 Spacer NSA5527-03-10 Item 17

5 Spacer NSA5527-03-11 Item 18

32 Washer ASNA2397-10L Item 14

17 Bolt NAS6603-1 Item 20

1 Bolt NAS6603-9 Item 21

2 Bolt NAS6603-32 Item 26

2 Bolt NAS6603-2 Item 29

5 Bolt NAS6603-17 Item 87

5 Bolt NAS6603-10 Item 94

2 Install the placards between FR53.6 and FR55 :

1 Placard F1131031620500 Item 88

1 Placard F1131031624400 Item 89

1 Placard F1131031620600 Item 90

1 Placard F1131031624500 Item 91

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3 Install the sensing elements between FR53.6 and FR55 :

FIN 24HF

1 Sensing Element 35597-3-255 Item 109

FIN 311HF

1 Sensing Element 35587-2-255 Item 110

FIN 25HF

1 Sensing Element 35627-2-255 Item 111

FIN 312HF

1 Sensing Element 35625-2-255 Item 112

2 Nut NSA5542-00 Item 15

2 Connector NSA5549-90 Item 85

55 Sleeve-Protective NSA5539S Item 13

NOTE: Secure the nuts Item 15 with wire-lock MS20995C32 Item 27.

(19) Subtask 364033-010-004-001 - If necessary, remove the ducts between FR39 and

FR40 for access.

Work Zones and Access Panels

Zone Access/Work location

190

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills AIRFRAME

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-010-801

Fig. A-FBPAA

Removal/Installation of the Ducts

Between FR39 and FR40 for Access

Sheet 01

(a) Remove :

Fig. A-FBPAA

(Refer to AMM Task 21-20-00-010-801)

1 Duct assy Item (125) Retain

1 Duct assy Item (126) Retain

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1 Duct assy Item (127) Retain

(20) Subtask 364033-831-013-001 - Install the new supports for the new harness

between FR39.1 and FR39.2.

Work Zones and Access Panels

Zone Access/Work location

190

Manpower Resources

Manhours 3.00

Minimum number of person 1

Subtask elapsed time 3.00

Skills AIRFRAME

Material necessary to do the job

Kit 364033A01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

63 ASNA2327-3-8 2 SUPPORT

64 F5391094700095 1 PLATE

65 NSA5456-3-8 1 SUPPORT

97 ASNA2050DCJ3215 14 RIVET

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Corrosion Inhibiting Brush

Consistency

09-013B As required

References

Fig. A-FBNAA

Installation of the Supports for the New

Harness

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

(a) At FR39.1, remove a support between STGR 37 and STGR 38.

Fig. A-FBNAA Sheet 02 and Fig. A-FBNAA Sheet 03

1 Remove :

2 Rivet Item (97) Discard

1 Support Item (88) Retain

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2 Install :

2 Rivet ASNA2050DCJ3215 Item 97

NOTE: Wet install the fasteners with :

Corrosion Inhibiting

Brush Consistency

09-013B As required

(b) At FR39.1, install a support between STGR 37 and STGR 38.

Fig. A-FBNAA Sheet 02 and Fig. A-FBNAA Sheet 03

1 Put the support Item (88) in position as shown on Fig. A-FBNAA Sheet 03.

2 Drill two holes on the structure to a diameter comprised between 3.25mm

(0.128in.) and 3.35mm (0.132in.) to match the holes of the support Item (88).

3 Install :

1 Support Item (88) Retained at

removal

2 Rivet ASNA2050DCJ3215 Item 97

NOTE: Wet install the fasteners with :

Corrosion Inhibiting

Brush Consistency

09-013B As required

(c) At FR39.2, install a plate between STGR 46 and STGR 47.

Fig. A-FBNAA Sheet 02 and Fig. A-FBNAA Sheet 04

1 Remove :

2 Rivet Item (97) Discard

1 Support Item (89) Retain

2 Put the plate Item 64 in position as shown on Fig. A-FBNAA Sheet 04.

3 Drill one hole on the plate Item 64 to a diameter comprised between 3.25mm

(0.128in.) and 3.35mm (0.132in.) to match the hole of the structure.

4 Drill three holes on the structure to a diameter comprised between 3.25mm

(0.128in.) and 3.35mm (0.132in.) to match the holes of the plate Item (64).

5 Install :

1 Plate F5391094700095 Item 64

4 Rivet ASNA2050DCJ3215 Item 97

NOTE: Wet install the fasteners with :

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Corrosion Inhibiting

Brush Consistency

09-013B As required

(d) At FR39.2, install two supports between STGR46 and STGR48.

Fig. A-FBNAA Sheet 02 and Fig. A-FBNAA Sheet 04

1 Put the supports Item 63 in position as shown on Fig. A-FBNAA Sheet 04.

2 Drill four holes on the structure to a diameter comprised between 3.25mm

(0.128in.) and 3.35mm (0.132in.) to match the holes of the supports Item 63.

3 Install :

2 Support ASNA2327-3-8 Item 63

4 Rivet ASNA2050DCJ3215 Item 97

NOTE: Wet install the fasteners with :

Corrosion Inhibiting

Brush Consistency

09-013B As required

(e) At FR39.1, install a support between STGR 39 and STGR 40.

Fig. A-FBNAA Sheet 02 and Fig. A-FBNAA Sheet 05

1 Put the support Item 65 in position as shown on Fig. A-FBNAA Sheet 05.

2 Drill two holes on the structure to a diameter comprised between 3.25mm

(0.128in.) and 3.35mm (0.132in.) to match the holes of the support Item 65.

3 Install :

1 Support NSA5456-3-8 Item 65

2 Rivet ASNA2050DCJ3215 Item 97

NOTE: Wet install the fasteners with :

Corrosion Inhibiting

Brush Consistency

09-013B As required

(21) Subtask 364033-831-014-001 - Install the Interconnecting Electrical Wire FIN 309HF

and 310HF, between the sensing elements.

Work Zones and Access Panels

Zone Access/Work location

150

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Manpower Resources

Manhours 3.00

Minimum number of person 1

Subtask elapsed time 3.00

Skills NON SPECIFIC

Material necessary to do the job

Kit 364033A02R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

14 ASNA2397-10L 1 WASHER

18 NSA5527-03-11 1 SPACER

92 NSA57304-643ADL 1 PLATE

155 NSA5516-04ND 1 CLAMP

168 NAS1801-3-22 1 SCREW

169 NSA935401-03 8 TIE

174 35301-74 1 CABLE

175 35301-75 2 CABLE

182 NSA5050-4 1 NUT

F1131031521900 1 PLACARD

F1131031522000 1 PLACARD

F9000095227895 BUNDLE

F9100095005595 1 PLACARD

References

Fig. A-FBCAA

Drilling of a New Hole in the Structure

between FR53.5 and FR53.6 on the LH

side and Installation of Sensing

Elements

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Fig. A-FCCAA

Installation of the Wiring of the New

Sensing Elements

Sheet 01

Sheet 02

(a) Put in position :

FIN 309HF

1 Cable-Electrical

Interconnecting

35301-74 Item 174

(b) Put in position :

FIN 310HF

1 Cable-Electrical

Interconnecting

35301-75 Item 175

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(c) Install the splice FIN 3593VS (PN E0360RK1816) between the FIN 309HF and the

FIN 310HF, supplied in :

Bundle F9000095227895

(d) Identify the splice FIN 3593VS with the identification sleeves and the identification

label supplied in :

1 Placard F9100095005595

and

Bundle F9000095227895

(e) On the fuselage close to the plugs, identify the FIN 309HF and the FIN 310HF with

:

1 Placard F1131031521900

and

1 Placard F1131031522000

(f) Identify the wire No. 3622-0543 of the FIN 310HF and the wire No. 3622-0544 of

the FIN 309HF with the identification sleeves supplied in :

1 Placard F9100095005595

(g) Modify the splice FIN 3503VS :

1 Before any disconnection, record the wires number associated to the FIN

137HF and the FIN 138HF.

2 Remove the splice FIN 3503VS between the FIN 137HF and the FIN 138HF :

FIN 3503VS

1 Splice Discard

NOTE: Retain the identification sleeves and the identification label of

the 3503VS and of the wires associated to the FIN 137HF and

the FIN 138HF.

3 Remove :

FIN 137HF

1 Cable-Electrical

Interconnecting

35301-74 Item (174) Discard

4 Maintain in position :

FIN 138HF

1 Cable-Electrical

Interconnecting

35301-75 Item (175)

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5 Put in position :

FIN 137HF

1 Cable-Electrical

Interconnecting

35301-75 Item 175

6 Install the new splice FIN 3503VS (PN E0360RK1816) between the FIN

137HF and the FIN 138HF, supplied in :

Bundle F9000095227895

NOTE: Identify the splice FIN 3503VS with the identification sleeves

and the identification label retained at removal.

NOTE: In accordance to the wires connections recorded at removal,

identify the wires associated to the FINs 137HF and 138HF

with the retained identification sleeves.

(h) Between Frame 53.5 and Frame 53.6 and as shown in Fig. A-FBCAA Sheet 01 and

Fig. A-FBCAA Sheet 03, install the FINs 137HF and 138HF and the FINs 309HF

and 310HF (spliced previously) with :

1 Spacer NSA5527-03-11 Item 18

1 Clamp NSA5516-04ND Item (155) Retained at

removal

1 Clamp NSA5516-04ND Item 155

1 Washer ASNA2397-10L Item 14

1 Screw NAS1801-3-22 Item 168

and attach it with :

8 Tie-Cable NSA935401-03 Item 169

NOTE: After connection, secure the FINs 137HF and 138HF and the FINs

309HF and 310HF with Wire-lock MS20995C32 item 27, (Refer to

Fig. A-FBCAA Sheet 05).

(i) Secure the FIN 310HF :

Refer to Fig. A-FBCAA Sheet 04

1 Remove :

1 Nut Discard

2 Install :

1 Plate-Attachment NSA57304-643ADL Item 92

With :

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1 Nut NSA5050-4 Item 182

3 Secure the new nut and the FIN 310HF with wire-lock MS20995C32 item 27,

(Refer to Fig. A-FBCAA Sheet 05).

(22) Subtask 364033-831-015-001 - Install the new Harness 2SG.

Work Zones and Access Panels

Zone Access/Work location

190

Manpower Resources

Manhours 26.00

Minimum number of person 2

Subtask elapsed time 13.00

Skills NON SPECIFIC

Material necessary to do the job

Kit 364033A02R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

14 ASNA2397-10L 4 WASHER

16 NSA5527-03-01 2 SPACER

18 NSA5527-03-11 1 SPACER

22 NSA5527-03-15 1 SPACER

131 NSA935808-03 24 WASHER

134 NSA935807-16 1 CLAMP

135 NSA935807-20 1 CLAMP

141 NSA5527-03-02 3 SPACER

150 NSA935807-04 30 CLAMP

151 NSA5159-17 19 STUD

152 NSA5527-03-08 19 SPACER

153 NSA935808-01 13 WASHER

154 NSA5050-3 28 NUT

157 NSA5159-10 1 STUD

158 NAS1801-3-9 4 SCREW

159 NAS1801-3-8 2 SCREW

163 NSA5159-27 5 STUD

165 NSA5527-03-05 1 SPACER

166 NAS1801-3-12 4 SCREW

167 NAS1801-3-10 3 SCREW

170 MS21042-3 4 NUT

171 NAS1801-3-17 2 SCREW

172 NAS1149F0332P 2 WASHER

173 NSA5527-03-12 6 SPACER

174 35301-74 1 CABLE

176 NSA5516-21ND 5 CLAMP

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ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

177 NSA5516-22ND 5 CLAMP

178 NSA5516-23ND 5 CLAMP

179 NSA5516-07ND 2 CLAMP

180 NSA5516-08ND 2 CLAMP

181 NSA5516-10ND 2 CLAMP

183 NSA934710E20 3 SPRING

184 NSA934710T11 2 FITTING

E0432A04 20 (M) CONDUIT

F1131031522100 1 PLACARD

F9000095227895 BUNDLE

References

Elec. Std. Practices Manual (ESPM) 20-43-42

Fig. A-FBMAA

Installation of the New Harness 2SG

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

Sheet 09

Sheet 10

Sheet 11

Sheet 12

Sheet 13

Sheet 14

Sheet 15

Sheet 16

Sheet 17

Sheet 18

Sheet 19

Sheet 20

Sheet 21

Sheet 22

Fig. A-FCCAA

Installation of the Wiring of the New

Sensing Elements

Sheet 01

Sheet 02

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(a) Install supports of new routing between 302HF located on the left hand side at

stringer 36 and Frame 40 and the 3520VP located on the right hand side at Frame

39.1 :

1 On the left hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03, Fig. A-FBMAA Sheet 04, Fig. A-FBMAA Sheet 05 and Fig. AFBMAA Sheet 06, along the Frame 39.1 and between Frame 39.1 and Frame

39.2, remove :

a For Section A-A :

7 Screw Item (130) Discard

7 Washer Item (131) Discard

7 Clamp Item (150) Retain

2 On the left hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03, Fig. A-FBMAA Sheet 04, Fig. A-FBMAA Sheet 05 and Fig. AFBMAA Sheet 06, along the Frame 39.1 and between Frame 39.1 and Frame

39.2, install :

a For Section B-B :

7 Stud NSA5159-17 Item 151

7 Clamp Item (150) Retained at

removal

7 Spacer NSA5527-03-08 Item 152

7 Clamp NSA935807-04 Item 150

7 Washer NSA935808-03 Item 131

7 Nut NSA5050-3 Item 154

b For Section C-C :

1 Stud NSA5159-17 Item 151

1 Clamp NSA935807-04 Item 150

1 Spacer NSA5527-03-08 Item 152

1 Clamp NSA935807-04 Item 150

1 Washer NSA935808-03 Item 131

1 Nut NSA5050-3 Item 154

NOTE: Install this hardware on the support Item 65 installed

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previously.

3 On the left hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03, Fig. A-FBMAA Sheet 04, Fig. A-FBMAA Sheet 05 , Fig. A-FBMAA

Sheet 07, Fig. A-FBMAA Sheet 08 and Fig. A-FBMAA Sheet 09, along the

Frame 39.1 and between Stringer 39 and 40, remove :

a For Section F-F :

1 Screw Item (130) Discard

1 Washer Item (131) Discard

1 Clamp Item (150) Retain

b For Section G-G :

1 Screw Item (132) Discard

1 Washer Item (133) Discard

1 Clamp Item (155) Retain

4 On the left hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03, Fig. A-FBMAA Sheet 04, Fig. A-FBMAA Sheet 05 , Fig. A-FBMAA

Sheet 07, Fig. A-FBMAA Sheet 08 and Fig. A-FBMAA Sheet 09, along the

Frame 39.1 and between Stringer 39 and 40, install :

a For Section H-H :

1 Stud NSA5159-17 Item 151

1 Clamp Item (150) Retained at

removal

1 Spacer NSA5527-03-08 Item 152

1 Clamp NSA935807-04 Item 150

1 Washer NSA935808-03 Item 131

1 Nut NSA5050-3 Item 154

b For Section J-J :

1 Stud NSA5159-17 Item 151

1 Clamp Item (155) Retained at

removal

1 Spacer NSA5527-03-08 Item 152

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1 Clamp NSA935807-04 Item 150

1 Washer NSA935808-03 Item 131

1 Nut NSA5050-3 Item 154

5 On the left hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 09, along the Frame 39.1 and between

Stringer 40 and 43, remove for detail F :

2 Screw Item (136) Discard

2 Washer Item (137) Discard

2 Clamp Item (135) Retain

2 Clamp Item (134) Retain

6 On the left hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 09, along the Frame 39.1 and between

Stringer 40 and 43, install for detail G :

2 Stud NSA5159-17 Item 151

2 Clamp Item (134) Retained at

removal

2 Clamp Item (135) Retained at

removal

2 Spacer NSA5527-03-08 Item 152

2 Clamp NSA935807-04 Item 150

2 Washer NSA935808-03 Item 131

2 Nut NSA5050-3 Item 154

7 On the left hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03, Fig. A-FBMAA Sheet 10 and Fig. A-FBMAA Sheet 11, along the

Frame 39.1 and between Stringers 44 and 45, remove :

a For Section K-K :

1 Nut Item (154) Discard

1 Washer Item (153) Discard

1 Clamp Item (138) Retain

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1 Spacer Item (152) Retain

1 Clamp Item (135) Retain

1 Clamp Item (134) Retain

1 Stud Item (151) Retain

Or

1 Nut Item (154) Discard

1 Washer Item (153) Discard

1 Clamp Item (138) Retain

1 Clamp Item (139) Retain

1 Spacer Item (152) Discard

1 Clamp Item (135) Retain

1 Clamp Item (134) Retain

1 Stud Item (151) Discard

8 On the left hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03, Fig. A-FBMAA Sheet 10 and Fig. A-FBMAA Sheet 11, along the

Frame 39.1 and between Stringers 44 and 45, install :

a For Section M-M :

1 Stud Item (151) Retained at

removal

1 Clamp Item (134) Retained at

removal

1 Clamp Item (135) Retained at

removal

1 Spacer Item (152) Retained at

removal

1 Clamp Item (138) Retained at

removal

1 Clamp NSA935807-04 Item 150

1 Washer NSA935808-03 Item 131

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1 Nut NSA5050-3 Item 154

Or

1 Stud NSA5159-27 Item 163

1 Clamp Item (134) Retained at

removal

1 Clamp Item (135) Retained at

removal

2 Spacer NSA5527-03-12 Item 173

1 Clamp Item (139) Retained at

removal

1 Clamp Item (138) Retained at

removal

1 Clamp NSA935807-04 Item 150

1 Washer NSA935808-03 Item 131

1 Nut NSA5050-3 Item 154

9 On the left hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03, Fig. A-FBMAA Sheet 10 and Fig. A-FBMAA Sheet 12, along the

Frame 39.1 and between Stringers 44 and 45, remove :

a For Section L-L :

1 Screw Item (130) Discard

1 Washer Item (153) Discard

1 Clamp Item (135) Retain

1 Clamp Item (134) Retain

10 On the left hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03, Fig. A-FBMAA Sheet 10 and Fig. A-FBMAA Sheet 12, along the

Frame 39.1 and between Stringers 44 and 45, install :

a For Section N-N :

1 Stud NSA5159-17 Item 151

1 Clamp Item (134) Retained at

removal

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 312

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SERVICE BULLETIN

1 Clamp Item (135) Retained at

removal

1 Spacer NSA5527-03-08 Item 152

1 Clamp NSA935807-04 Item 150

1 Washer NSA935808-03 Item 131

1 Nut NSA5050-3 Item 154

11 On the left hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03, Fig. A-FBMAA Sheet 13 and Fig. A-FBMAA Sheet 14, along the

Frame 39.1 and between Stringers 46 and 48, remove :

a For Section P-P :

1 Nut Item (154) Discard

1 Washer Item (153) Discard

1 Clamp Item (139) Retain

1 Spacer Item (152) Retain

1 Clamp Item (135) Retain

1 Clamp Item (134) Retain

1 Stud Item (151) Discard

Or

1 Nut Item (154) Discard

1 Washer Item (153) Discard

1 Clamp Item (138) Retain

1 Clamp Item (139) Retain

1 Spacer Item (152) Discard

1 Clamp Item (135) Retain

1 Clamp Item (134) Retain

1 Stud Item (151) Discard

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 313

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@A340

SERVICE BULLETIN

12 On the left hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03, Fig. A-FBMAA Sheet 13 and Fig. A-FBMAA Sheet 14, along the

Frame 39.1 and between Stringers 46 and 48, install :

a For Section R-R :

1 Stud NSA5159-17 Item 151

1 Clamp Item (134) Retained at

removal

1 Clamp Item (135) Retained at

removal

1 Spacer Item (152) Retained at

removal

1 Clamp Item (139) Retained at

removal

1 Clamp NSA935807-04 Item 150

1 Washer NSA935808-03 Item 131

1 Nut NSA5050-3 Item 154

Or

1 Stud NSA5159-27 Item 163

1 Clamp Item (134) Retained at

removal

1 Clamp Item (135) Retained at

removal

2 Spacer NSA5527-03-12 Item 173

1 Clamp Item (139) Retained at

removal

1 Clamp Item (138) Retained at

removal

1 Clamp NSA935807-04 Item 150

1 Washer NSA935808-03 Item 131

1 Nut NSA5050-3 Item 154

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 314

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@A340

SERVICE BULLETIN

13 On the left hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03, Fig. A-FBMAA Sheet 13 and Fig. A-FBMAA Sheet 15, along the

Frame 39.1 and between Stringers 46 and 48, remove :

a For Section Q-Q :

1 Nut Item (154) Discard

1 Washer Item (153) Discard

1 Clamp Item (135) Retain

1 Spacer Item (152) Retain

1 Clamp Item (134) Retain

1 Clamp Item (139) Retain

1 Stud Item (151) Retain

Or

1 Nut Item (154) Discard

1 Washer Item (153) Discard

1 Clamp Item (138) Retain

1 Clamp Item (135) Retain

1 Spacer Item (152) Discard

1 Clamp Item (134) Retain

1 Clamp Item (139) Retain

1 Stud Item (144) Discard

14 On the left hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03, Fig. A-FBMAA Sheet 13 and Fig. A-FBMAA Sheet 15, along the

Frame 39.1 and between Stringers 46 and 48, install :

a For Section S-S :

1 Stud Item (151) Retained at

removal

1 Clamp NSA935807-04 Item 150

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 315

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@A340

SERVICE BULLETIN

1 Clamp Item (134) Retained at

removal

1 Spacer Item (152) Retained at

removal

1 Clamp Item (139) Retained at

removal

1 Clamp Item (135) Retained at

removal

1 Washer NSA935808-01 Item 153

1 Nut NSA5050-3 Item 154

Or

1 Stud NSA5159-27 Item 163

1 Clamp NSA935807-04 Item 150

1 Clamp Item (134) Retained at

removal

2 Spacer NSA5527-03-12 Item 173

1 Clamp Item (139) Retained at

removal

1 Clamp Item (138) Retained at

removal

1 Clamp Item (135) Retained at

removal

1 Washer NSA935808-01 Item 153

1 Nut NSA5050-3 Item 154

15 On the left hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 16, along the Frame 39.1 and between

Stringers 49 and 52, remove for detail K :

2 Screw Item (132) Discard

2 Washer Item (153) Discard

2 Clamp Item (138) Retain

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 316

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SERVICE BULLETIN

16 On the left hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 16, along the Frame 39.1 and between

Stringers 49 and 52, install for detail L :

2 Stud NSA5159-17 Item 151

2 Clamp Item (138) Retained at

removal

2 Spacer NSA5527-03-08 Item 152

2 Clamp NSA935807-04 Item 150

2 Washer NSA935808-03 Item 131

2 Nut NSA5050-3 Item 154

17 On the left hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 17, along the Frame 39.1 and between

Stringers 52 and 54, remove for Section T-T :

1 Nut Item (154) Discard

1 Washer Item (153) Discard

1 Clamp Item (138) Retain

1 Spacer Item (141) Retain

1 Clamp Item (138) Retain

1 Stud Item (140) Retain

18 On the left hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 17, along the Frame 39.1 and between

Stringers 52 and 54, install for Section U-U :

1 Stud Item (140) Retained at

removal

1 Clamp Item (138) Retained at

removal

1 Spacer Item (141) Retained at

removal

1 Clamp Item (138) Retained at

removal

1 Clamp NSA935807-04 Item 150

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 317

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@A340

SERVICE BULLETIN

1 Washer NSA935808-03 Item 131

1 Nut NSA5050-3 Item 154

19 On the right hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 18, along the Frame 39.1 and near the

Stringers 54, remove for detail N :

1 Screw Item (142) Discard

1 Washer Item (153) Discard

1 Clamp Item (138) Retain

20 On the right hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 18, along the Frame 39.1 and near the

Stringers 54, install for detail P :

1 Stud NSA5159-17 Item 151

1 Clamp Item (138) Retained at

removal

1 Spacer NSA5527-03-08 Item 152

1 Clamp NSA935807-04 Item 150

1 Washer NSA935808-03 Item 131

1 Nut NSA5050-3 Item 154

21 On the right hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 18, along the Frame 39.1 and between

Stringers 54 and 48, remove for detail Q :

3 Screw Item (142) Discard

3 Washer Item (153) Discard

3 Clamp Item (138) Retain

22 On the right hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 18, along the Frame 39.1 and between

Stringers 54 and 48, install for detail R :

3 Clamp NSA935807-04 Item 150

3 Clamp Item (138) Retained at

removal

3 Washer NSA935808-01 Item 153

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 318

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SERVICE BULLETIN

3 Screw NAS1801-3-9 Item 158

23 On the right hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 18, between the Frame 39.1 and Frame

39.2 and between Stringers 48 and 46, install for detail S :

2 Clamp NSA935807-04 Item 150

2 Washer NSA935808-03 Item 131

2 Screw NAS1801-3-8 Item 159

NOTE: Install this hardware on the support Item 63 installed

previously.

24 On the right hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 19, between the Frame 39.1 and Frame

39.2 and between Stringers 48 and 46, install for Section W-W :

2 Spacer NSA5527-03-02 Item 141

2 Clamp NSA5516-07ND Item 179

or

2 Clamp NSA5516-08ND Item 180

or

2 Clamp NSA5516-10ND Item 181

and

2 Washer NAS1149F0332P Item 172

2 Screw NAS1801-3-17 Item 171

NOTE: Depends on aircraft configuration, use the PN NSA5516-07ND

or NSA5516-08ND or NSA5516-10ND for Item 170.

NOTE: Install this hardware on the support Item 64 installed

previously.

25 On the right hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 19, between the Frame 39.1 and Frame

39.2 and between Stringers 48 and 46, install for Section V-V :

1 Stud NSA5159-27 Item 163

1 Spacer NSA5527-03-01 Item 16

1 Clamp NSA935807-16 Item 134

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 319

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SERVICE BULLETIN

1 Spacer NSA5527-03-08 Item 152

1 Clamp NSA935807-20 Item 135

1 Washer NSA935808-01 Item 153

1 Nut NSA5050-3 Item 154

NOTE: Install this hardware on the support Item 64 installed

previously.

26 On the right hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 20, between the Frame 39.1 and Frame

39.2 and between Stringers 47 and 46, remove for detail T :

1 Screw Item (136) Discard

1 Washer Item (153) Discard

1 Clamp Item (135) Retain

1 Clamp Item (134) Retain

27 On the right hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 20, between the Frame 39.1 and Frame

39.2 and between Stringers 47 and 46, install for detail U :

1 Stud NSA5159-17 Item 151

1 Spacer NSA5527-03-02 Item 141

1 Clamp Item (134) Retained at

removal

1 Spacer NSA5527-03-05 Item 165

1 Clamp Item (135) Retained at

removal

1 Washer NSA935808-01 Item 153

1 Nut NSA5050-3 Item 154

28 On the right hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 20, between the Frame 39.1 and Frame

39.2 and between Stringers 47 and 46, remove for detail Y :

1 Screw Item (143) Discard

1 Washer Item (133) Discard

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 320

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SERVICE BULLETIN

1 Clamp Item (155) Retain

1 Clamp Item (155) Retain

29 On the right hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 20, between the Frame 39.1 and Frame

39.2 and between Stringers 47 and 46, install for detail Z :

1 Stud NSA5159-27 Item 163

1 Clamp Item (155) Retained at

removal

1 Clamp Item (155) Retained at

removal

1 Spacer NSA5527-03-08 Item 152

1 Spacer NSA5527-03-15 Item 22

1 Clamp NSA935807-04 Item 150

1 Washer NSA935808-03 Item 131

1 Nut NSA5050-3 Item 154

30 On the right hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 20, between the Frame 39.1 and Frame

39.2 and between Stringers 46 and 45, remove for detail W :

1 Screw Item (136) Discard

1 Washer Item (153) Discard

1 Clamp Item (135) Retain

1 Clamp Item (134) Discard

31 On the right hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 20, between the Frame 39.1 and Frame

39.2 and between Stringers 46 and 45, install for detail X :

1 Stud NSA5159-10 Item 157

And

1 Clamp NSA5516-21ND Item 176

Or

1 Clamp NSA5516-22ND Item 177

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 321

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SERVICE BULLETIN

Or

1 Clamp NSA5516-23ND Item 178

And

1 Spacer NSA5527-03-01 Item 16

1 Spacer NSA5527-03-08 Item 152

1 Clamp Item (135) Retained at

removal

1 Washer NSA935808-01 Item 153

1 Nut NSA5050-3 Item 154

NOTE: Depends on aircraft configuration, use the PN NSA5516-21ND

or NSA5516-22ND or NSA5516-23ND for Item 166.

32 On the right hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 21, between the Frame 39.1 and Frame

39.2 and between Stringers 44 and 43, remove for detail AA :

1 Screw Item (136) Discard

1 Washer Item (153) Discard

1 Clamp Item (135) Retain

1 Clamp Item (134) Discard

33 On the right hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 21, between the Frame 39.1 and Frame

39.2 and between Stringers 44 and 43, install for detail AB :

1 Stud NSA5159-17 Item 151

And

1 Clamp NSA5516-21ND Item 176

Or

1 Clamp NSA5516-22ND Item 177

Or

1 Clamp NSA5516-23ND Item 178

And

1 Spacer NSA5527-03-11 Item 18

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 322

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@A340

SERVICE BULLETIN

1 Clamp Item (135) Retained at

removal

1 Washer NSA935808-01 Item 153

1 Nut NSA5050-3 Item 154

NOTE: Depends on aircraft configuration, use the PN NSA5516-21ND

or NSA5516-22ND or NSA5516-23ND for Item 166.

34 On the right hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 21, between the Frame 39.1 and Frame

39.2 and between Stringers 42 and 38, remove for detail AC :

3 Screw Item (136) Discard

3 Washer Item (153) Discard

3 Clamp Item (135) Retain

3 Clamp Item (134) Discard

35 On the right hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 21, between the Frame 39.1 and Frame

39.2 and between Stringers 42 and 38, install for detail AD :

3 Clamp NSA5516-21ND Item 176

Or

3 Clamp NSA5516-22ND Item 177

Or

3 Clamp NSA5516-23ND Item 178

And

3 Clamp Item (135) Retained at

removal

3 Washer NSA935808-01 Item 153

3 Screw NAS1801-3-10 Item 167

NOTE: Depends on aircraft configuration, use the PN NSA5516-21ND

or NSA5516-22ND or NSA5516-23ND for Item 166.

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 323

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SERVICE BULLETIN

36 On the right hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 21, along the Frame 39.1 and between

Stringers 38 and 37, remove for detail AE :

1 Screw Item (153) Discard

1 Washer Item (142) Discard

1 Clamp Item (135) Retain

37 On the right hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 21, between the Frame 39.1 and Frame

39.2 and between Stringers 38 and 37, install for detail AF :

1 Clamp Item (135) Retained at

removal

1 Washer NSA935808-01 Item 153

1 Screw NAS1801-3-9 Item 158

NOTE: Install this hardware on the support Item (88) installed

previously.

(b) Install the new route 2SG between FIN 302HF located on the left hand side at

stringer 36 and Frame 40 and the FIN 3520VC located in the avionics compartment

:

1 Remove the pressure seal 3520VP :

Refer to ESPM 20-43-42 and to Fig. A-FBMAA Sheet 22

a Remove :

2 Fitting-Seal NSA934710T11 Item (184) Discard

And

3 Spring NSA934710E20 Item (183) Discard

Attached with :

4 Screw NAS1801-3-12 Item (166) Discard

4 Washer ASNA2397-10L Item (14) Discard

4 Nut MS21042-3 Item (170) Discard

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 324

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2 Put in position :

FIN 301HF

1 Cable-Electrical

Interconnecting

35301-74 Item 174

3 Install :

20 (M) Conduit E0432A04

4 Using supports installed at paragraph 3.C.(20).(a), route the wire No.

3622-0540 spliced at paragraph 3.C.(20).(b).2, from FIN 301HF located on the

left hand side at stringer 36 and at Frame 40, through pressure seal 3520VP,

to 3520VC located in avionics compartment as shown in Fig. A-FCCAA Sheet

01 and in Fig. A-FBMAA Sheet 01.

NOTE: The route 2SG rejoins route 2S on the right hand side at

stringer 46 between Frame 39.1 and Frame 39.2 as shown in

Fig. A-FBMAA Sheet 17.

5 Connect the wire No. 3622-0540 as shown on the wiring diagram, Fig. AFCCAA Sheet 01 and as given in the Hook-up Chart lines :

- 1 and 2 (Refer to Fig. A-FCCAA Sheet 02).

NOTE: Use the contacts supplied in :

Bundle F9000095227895

6 Install the splice FIN 3591VS (PN NSA936809RG0002) between the FIN

301HF and the wire No. 3622-0540 supplied in :

Bundle F9000095227895

NOTE: After connection, Secure the FIN 301HF and FIN 302HF with

Wire-lock MS20995C32 item 27.

7 Install the pressure seal 3520VP :

Refer to ESPM 20-43-42 and to Fig. A-FBMAA Sheet 22

a Install :

2 Fitting-Seal NSA934710T11 Item 184

And

3 Spring NSA934710E20 Item 183

Attach with :

4 Screw NAS1801-3-12 Item 166

4 Washer ASNA2397-10L Item 14

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 325

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SERVICE BULLETIN

4 Nut MS21042-3 Item 170

8 Identify the splice FIN 3591VS with the identification sleeves and the

identification label supplied in :

Bundle F9000095227895

9 On the fuselage close to the plugs, identify the FIN 301HF with :

1 Placard F1131031522100

(23) Subtask 364033-831-201-001 - Install the electrical wiring in the FWD cargo

compartment

Work Zones and Access Panels

Zone Access/Work location

130 Work location from Frame 19 to Frame 37.1

Manpower Resources

Manhours 7.50

Minimum number of person 2

Subtask elapsed time 3.50

Skills ELECTRICAL

Material necessary to do the job

Kit 364033D01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

400 F9297000500000 1 EQUIPMNT

402 F9237000207400 2 PLCRDSET

404 NSA935401-03 100 TIE

405 NSA935401-04 100 TIE

406 NSA935401-05 100 TIE

407 NSA935401-10 100 TIE

References

Fig. A-GBAAA

Installation of the Electrical Wiring in the

FWD Cargo Compartment

Sheet 01

Fig. A-GHAAA

Hook-up Chart

Sheet 01

Fig. A-GHBAA

Hook-up Chart

Sheet 01

Fig. A-GWAAA

Wiring Diagram

Sheet 01

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 326

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SERVICE BULLETIN

(a) Install the electrical wiring in the FWD cargo compartment

1 Install the electrical wires:

Refer to Fig. A-GBAAA Sheet 01

Refer to Fig. A-GHAAA Sheet 01, Line 1 thru 2, END 1,

Refer to Fig. A-GWAAA Sheet 01

supplied with:

1 Equipment AssyElectricalF9297000500000 Item 400

2 Attach the electrical wires with:

Refer to Fig. A-GBAAA Sheet 01

100 Tie-Cable NSA935401-03 Item 404

100 Tie-Cable NSA935401-04 Item 405

100 Tie-Cable NSA935401-05 Item 406

100 Tie-Cable NSA935401-10 Item 407

Install the identification placards

2 Placard Set F9237000207400 Item 402

(24) Subtask 364033-831-202-001 - Install the electrical wiring in the AFT cargo

compartment and Bulk cargo compartment

Work Zones and Access Panels

Zone Access/Work location

From 150 Work location Frame 55

To 170 Work location Frame 80

Manpower Resources

Manhours 11.00

Minimum number of person 2

Subtask elapsed time 5.50

Skills ELECTRICAL

Material necessary to do the job

Kit 364033D01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

400 F9297000500000 1 EQUIPMNT

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 327

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SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

402 F9237000207400 4 PLCRDSET

404 NSA935401-03 100 TIE

405 NSA935401-04 100 TIE

406 NSA935401-05 100 TIE

407 NSA935401-10 100 TIE

References

Fig. A-GBBAA

Installation of the Electrical Wiring in the

AFT Cargo Compartment

Sheet 01

Sheet 02

Fig. A-GHAAA

Hook-up Chart

Sheet 01

Fig. A-GHBAA

Hook-up Chart

Sheet 01

Fig. A-GWAAA

Wiring Diagram

Sheet 01

(a) Install the electrical wiring in the AFT cargo compartment and Bulk cargo

compartment

1 Install the electrical wires on 5866VB between Frame 55 thru Frame 80/82:

Refer to Fig. A-GBBAA Sheet 01

Refer to Fig. A-GWAAA Sheet 01

Refer to Fig. A-GHAAA Sheet 01, Line 1 thru 3, END 1,

supplied with:

1 Equipment AssyElectricalF9297000500000 Item 400

2 Attach the electrical wires with:

Refer to Fig. A-GBBAA Sheet 01

100 Tie-Cable NSA935401-03 Item 404

100 Tie-Cable NSA935401-04 Item 405

100 Tie-Cable NSA935401-05 Item 406

100 Tie-Cable NSA935401-10 Item 407

Install the identification placards

4 Placard Set F9237000207400 Item 402

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 328

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SERVICE BULLETIN

3 Route the electrical wires through the thermal insulator at Frame 80/82:

Refer to Fig. A-GBBAA Sheet 02

1 Insulator-Cable

Protection

ABS0596S006 Item (403)

(25) Subtask 364033-831-203-001 - Modify the electrical wiring in the AFT cargo

compartment, Bulk cargo compartment and Rear fuselage section

Manpower Resources

Manhours 4.50

Minimum number of person 1

Subtask elapsed time 4.50

Skills ELECTRICAL

References

Fig. A-GBCAA

Preparation for the Electrical Wiring

Installation in the Rear Fuselage Section

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

Sheet 09

Sheet 10

Fig. A-GHAAA

Hook-up Chart

Sheet 01

Fig. A-GHBAA

Hook-up Chart

Sheet 01

(a) Remove the pressure seal 5208VP from the pressure Frame at Frame 80/82

Refer to Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet 03

Remove:

1 Plate F9249011000200 Item (410) Retain

1 Plate F9249011000400 Item (411) Retain

2 Bulkhead Item (415) Discard

8 Screw Item (416) Discard

12 Washer Item (417) Discard

4 Washer Item (418) Discard

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 329

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4 Nut Item (419) Discard

or if alternate installed remove:

12 Washer Item (417) Discard

4 Washer Item (418) Discard

4 Nut Item (419) Discard

4 Screw Item (420) Discard

2 Screw Item (423) Discard

(b) Remove the lightning protection of the electrical bundle 5886VB at Frame 90

Refer to Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet 08

1 At Frame 90 loosen the electrical receptacle 5215VC, Item (435).

Refer to Fig. A-GBCAA Sheet 04 thru Fig. A-GBCAA Sheet 05

4 Screw Item (430) Discard

4 Washer Item (431) Discard

4 Nut Item (432) Discard

2 Disconnect the electrical wires end from the electrical receptacle 5215VC.

Refer to Fig. A-GBCAA Sheet 04 thru Fig. A-GBCAA Sheet 05

Refer to Fig. A-GHAAA Sheet 01 END 2, Line 4 thru 25 Fig. A-GHBAA Sheet

01 END 2, Line 1 and 2

Remove:

1 Receptacle Item (435) Retain

3 Remove from Frame 91

Refer to Fig. A-GBCAA Sheet 04 thru Fig. A-GBCAA Sheet 05

1 Screw Item (314) Discard

1 Washer Item (417) Discard

1 Clamp Item (437) Discard

1 Clip nut Item (353) Discard

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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SERVICE BULLETIN

4 Remove the lightning protection from the electrical bundle 5886VB at Frame

90

Refer to Fig. A-GBCAA Sheet 04 thru Fig. A-GBCAA Sheet 08

8 Screw Item (314) Discard

12 Washer Item (417) Discard

3 Nut Item (419) Discard

21 Clamp Item (437) Retain

3 Spacer Item (442) Retain

1 Clamp Item (443) Retain

4 Screw Item (444) Discard

1 Clip nut Item (448) Discard

or if alternate installed remove:

1 Washer Item (417) Discard

2 Spacer Item (442) Retain

3 Clamp Item (437) Retain

1 Clip nut Item (439) Discard

1 Screw Item (501) Discard

(c) Disconnect the electrical wiring 5865VB from the APU overhead leak detection

system at Frame 93

Refer to Fig. A-GBCAA Sheet 01, Fig. A-GBCAA Sheet 09 thru Fig. A-GBCAA

Sheet 10

Refer to Fig. A-GHAAA Sheet 01

1 Remove between Frame 92 thru Frame 93:

Refer to Fig. A-GBCAA Sheet 09 thru Fig. A-GBCAA Sheet 10

1 Washer Item (417) Discard

1 Nut Item (419) Discard

2 Clamp Item (437) Retain

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 331

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SERVICE BULLETIN

1 Screw Item (449) Discard

1 Spacer Item (464) Retain

1 Screw Item (465) Discard

1 Nut Item (470) Discard

1 Washer Item (471) Discard

2 Remove from Frame 93:

Refer to Fig. A-GBCAA Sheet 09

2 Washer Item (417) Discard

4 Spacer Item (442) Retain

2 Clamp Item (437) Retain

2 Clip nut Item (448) Discard

2 Screw Item (501) Discard

3 Remove the electrical splice 5151VSA from Frame 93:

Refer to Fig. A-GBCAA Sheet 09 thru Fig. A-GBCAA Sheet 10

Refer to Fig. A-GHAAA Sheet 01 END 2, Line 4 and 5

1 Sleeve Item (479) Discard

1 Sleeve Item (480) Discard

1 Splice Item (481) Discard

(26) Subtask 364033-831-205-001 - Install an additional profile in the Rear fuselage

section

Work Zones and Access Panels

Zone Access/Work location

310 Work location from Frame 90 to Frame 91

Stringer 6RH

Manpower Resources

Manhours 3.00

Minimum number of person 1

Subtask elapsed time 3.00

Skills AIRFRAME

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 332

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SERVICE BULLETIN

Material necessary to do the job

Kit 364033D03R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

314 NAS1801-3-8 2 SCREW

460 F5397083308600 1 SECTION

461 MS21047L3 1 NUT

462 EN6101AD3-08 2 RIVET

463 NAS1149D0332J 2 WASHER

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Corrosion Inhibitive interfay

Sealant

09-005

Corrosion Inhibiting, Fillet

Consistency

09-016 As required

Corrosion Inhibiting low

Adhesion Sealant

09-018

References

Fig. A-GBEAA

Installation of the Bracket between FR90

and FR91

Sheet 01

(a) Install an additional profile in the Rear fuselage section

1 Between Frame 90 thru Frame 91, at RH STGR6, temporarily put into position

Refer to Fig. A-GBEAA Sheet 01

1 Section Assy F5397083308600 Item 460

2 Transfer drill the holes and open holes to final dimension and install:

1 Nut MS21047L3 Item 461

with:

2 Rivet EN6101AD3-08 Item 462

NOTE: For dimensions refer to the table on Fig. A-GBEAA Sheet 01.

3 Between Frame 90 thru Frame 91, at RH STGR6, install:

1 Section Assy F5397083308600 Item 460

with:

2 Screw NAS1801-3-8 Item 314

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 333

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SERVICE BULLETIN

2 Washer NAS1149D0332J Item 463

and protect the surface with:

Corrosion Inhibitive

interfay Sealant

09-005 As required

and

Corrosion Inhibiting,

Fillet Consistency

09-016 As required

, and seal the edges with:

Corrosion Inhibiting

low Adhesion

Sealant

09-018 As required

(27) Subtask 364033-831-204-001 - Install the electrical wiring in the rear fuselage

section

Work Zones and Access Panels

Zone Access/Work location

310 Work location from Frame 80/82 to Frame 93

Manpower Resources

Manhours 14.00

Minimum number of person 2

Subtask elapsed time 7.00

Skills ELECTRICAL

Material necessary to do the job

Kit 364033D01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

314 NAS1801-3-8 8 SCREW

320 NSA5527-03-02 5 SPACER

350 AS21919WCH13 6 CLAMP

351 MS21919WCH14 1 CLAMP

352 MS21919WCH8 1 CLAMP

353 NSA5067-3-1 1 NUT

400 F9297000500000 1 EQUIPMNT

402 F9237000207400 10 PLCRDSET

404 NSA935401-03 100 TIE

405 NSA935401-04 100 TIE

406 NSA935401-05 50 TIE

415 NSA934710T14 2 FITTING

416 NAS1801-3-9 8 SCREW

417 NAS1149C0332R 24 WASHER

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 334

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SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

418 NAS1149D0363K 4 WASHER

419 NAS1291C3M 10 NUT

420 NAS1102-3-10 4 SCREW

423 NAS1801-3-10 2 SCREW

430 NAS1100-04-6 4 SCREW

431 NAS1149CN416R 4 WASHER

432 MS21042-04 4 NUT

439 NSA5066-3-1 1 NUT

444 NAS1801-3-18 3 SCREW

448 NSA5066-3-2 1 NUT

449 NAS1801-08-8 2 SCREW

451 F9249016013200 1 PROTSYS

465 NAS1801-3-15 1 SCREW

469 ASNA0182-4ADL 2 STRIP

470 NAS1291C08M 3 NUT

471 NAS1149CN816R 5 WASHER

472 ASNA0182-3ADL 1 STRIP

475 NAS1801-08-36 2 SCREW

476 NSA5066-08-1 2 NUT

479 E0718-01 0.06 TUBING

480 NSA937210MB0300 0.1 TUBING

481 NSA936809RG0001 2 SPLICE

485 NSA934710E20 3 SPRING

488 E0126-06L 0.2 TUBING

489 F9249016510800 1 PROTSYS

492 ABS0580A17P 1 FITTING

493 NAS1801-3-21 2 SCREW

494 NSA935808C03 2 WASHER

496 NSA5527-03-08D 2 SPACER

501 NAS1801-3-27 2 SCREW

510 E0126-01L 0.35 TUBING

511 F9249016110900 1 PROTSYS

515 AS21919WCH07 1 CLAMP

517 ABS0513-09 1 SUPPORT

518 ABS0520-07P 1 NUT

521 AS21919WCH14 1 CLAMP

528 NAS1801-08-12 1 SCREW

536 AS21919WCH02 3 CLAMP

537 AS21919WCH09 1 CLAMP

843 MS21919WCH12 1 CLAMP

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 335

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SERVICE BULLETIN

References

Fig. A-GBDAA

Installation of the Electrical Wiring in the

Rear Fuselage Section

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

Sheet 09

Sheet 10

Sheet 11

(a) Install the electrical wire in the rear fuselage section

1 Install the electrical wire, Item 400, on 5866VB between Frame 80/82 thru

Frame 90

Refer to Fig. A-GBDAA Sheet 01

1 Equipment AssyElectricalF9297000500000 Item 400

Attach the wire with:

2 Placard Set F9237000207400 Item 402

100 Tie-Cable NSA935401-03 Item 404

100 Tie-Cable NSA935401-04 Item 405

50 Tie-Cable NSA935401-05 Item 406

2 Install the electrical wire on 5866VB with the pressure seal 5208VP at Frame

80/82

Refer to Fig. A-GBDAA Sheet 01 thru Fig. A-GBDAA Sheet 03

Install:

1 Plate F9249011000200 Item (410) Retained at

removal

1 Plate F9249011000400 Item (411) Retained at

removal

with:

2 Fitting-Seal NSA934710T14 Item 415

8 Screw NAS1801-3-9 Item 416

12 Washer NAS1149C0332R Item 417

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 336

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4 Washer NAS1149D0363K Item 418

4 Nut NAS1291C3M Item 419

4 Screw NAS1102-3-10 Item 420

2 Screw NAS1801-3-10 Item 423

NOTE: Alternative to two of the, Item 416.

3 Spring NSA934710E20 Item 485

3 Install the lightning protection of the electrical bundle 5886VB at Frame 90.

Attach to the wires on 5866VB leaving thru the 3 way transition at Frame 90

Refer to Fig. A-GBDAA Sheet 04

0.1 Tubing-Heat-Shrinkable E0126-06L Item 488

NOTE: Cut the sleeve to the necessary length.

4 Route the wires on 5866VB between Frame 90 thru Frame 91

Refer to Fig. A-GBDAA Sheet 04, Fig. A-GBDAA Sheet 08 thru Fig. A-GBDAA

Sheet 09

Install:

1 Protection SystemLightningF9249016510800 Item 489

with:

1 Washer NAS1149C0332R Item 417

1 Screw NAS1801-3-18 Item 444

1 Clamp AS21919WCH13 Item 350

1 Clamp Item (437) Retained at

removal

1 Spacer Item (442) Retained at

removal

5 Route the electrical wires:

Refer to Fig. A-GBDAA Sheet 04 and Fig. A-GBDAA Sheet 08

1 Fitting-Conduit ABS0580A17P Item 492

and install, Item 492, at Frame 90 with:

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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1 Clamp MS21919WCH14 Item 351

2 Nut NAS1291C3M Item 419

1 Strip ASNA0182-4ADL Item 469

2 Screw NAS1801-3-21 Item 493

2 Washer NSA935808C03 Item 494

2 Spacer NSA5527-03-08D Item 496

1 Clamp MS21919WCH12 Item 843

6 Route the electrical wires on 5866VB between Frame 90 thru Frame 91 to

connector 5215VC

Refer to Fig. A-GBDAA Sheet 04 thru Fig. A-GBDAA Sheet 08

Reinstall the connector 5215VC

1 Receptacle Item (435) Retained at

removal

attached with:

4 Screw NAS1100-04-6 Item 430

4 Washer NAS1149CN416R Item 431

4 Nut MS21042-04 Item 432

and install:

1 Screw NAS1801-3-8 Item 314

1 Washer NAS1149C0332R Item 417

2 Clamp Item (437) Retained at

removal

1 Nut-Clip NSA5066-3-2 Item 448

or alternative install:

1 Washer NAS1149C0332R Item 417

3 Clamp Item (437) Retained at

removal

1 Nut-Clip NSA5066-3-1 Item 439

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 338

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SERVICE BULLETIN

2 Spacer Item (442) Retained at

removal

1 Screw NAS1801-3-27 Item 501

and install:

12 Clamp Item (437) Retained at

removal

2 Spacer Item (442) Retained at

removal

5 Clamp AS21919WCH13 Item 350

8 Washer NAS1149C0332R Item 417

7 Screw NAS1801-3-8 Item 314

1 Screw NAS1801-3-27 Item 501

2 Spacer NSA5527-03-02 Item 320

3 Nut NAS1291C3M Item 419

2 Screw NAS1801-3-18 Item 444

1 Nut NSA5067-3-1 Item 353

7 Route the wire, Item 400, from the 3 way transition, Item 492, to the splice

5410VS and route to the wire 5866VB with:

Refer to Fig. A-GBDAA Sheet 04 and Fig. A-GBDAA Sheet 08

1 Protection SystemLightningF9249016013200 Item 451

1 Protection SystemLightningF9249016510800 Item 489

1 Protection SystemLightningF9249016110900 Item 511

0.1 Tubing-Heat-Shrinkable E0126-06L Item 488

0.35 Tubing-Heat-Shrinkable E0126-01L Item 510

NOTE: Cut the sleeve to the necessary length.

and install:

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 339

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SERVICE BULLETIN

8 Placard Set F9237000207400 Item 402

8 Install the protection, Item 511, at Frame 93 with:

1 Nut ABS0520-07P Item 518

1 Support-Strain Relief ABS0513-09 Item 517

9 Install the electrical wire at Frame 93on 5865VB and 5866VB with:

Refer to Fig. A-GBDAA Sheet 01 and Fig. A-GBDAA Sheet 10 thru Fig. AGBDAA Sheet 11

Install:

3 Spacer NSA5527-03-02 Item 320

1 Clamp MS21919WCH8 Item 352

1 Washer NAS1149C0332R Item 417

1 Nut NAS1291C3M Item 419

6 Clamp Item (437) Retained at

removal

5 Spacer Item (442) Retained at

removal

2 Screw NAS1801-08-8 Item 449

1 Screw NAS1801-3-15 Item 465

1 Strip ASNA0182-4ADL Item 469

3 Nut NAS1291C08M Item 470

5 Washer NAS1149CN816R Item 471

1 Strip-Bonding ASNA0182-3ADL Item 472

2 Screw NAS1801-08-36 Item 475

2 Nut-Clip NSA5066-08-1 Item 476

1 Clamp AS21919WCH07 Item 515

1 Clamp AS21919WCH14 Item 521

1 Screw NAS1801-08-12 Item 528

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 340

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SERVICE BULLETIN

3 Clamp AS21919WCH02 Item 536

1 Clamp AS21919WCH09 Item 537

for the wire connection install:

0.06 Tubing-Heat-Shrinkable E0718-01 Item 479

0.1 Tubing-Heat Shrink NSA937210MB0300 Item 480

2 Splice NSA936809RG0001 Item 481

(28) Subtask 364033-831-206-001 - Remove the sensing elements in the AFT and Bulk

cargo compartments

Work Zones and Access Panels

Zone Access/Work location

From 160 Work location Frame 55

To 310 Work location Frame 83

Manpower Resources

Manhours 5.25

Minimum number of person 1

Subtask elapsed time 5.25

Skills ELECTRICAL

References

Fig. A-GBFAA

Removal of the Sensing Elements in the

Bulk and AFT Cargo Compartments

Sheet 01

Sheet 02

Sheet 03

(a) Remove the sensing elements from the APU bleed air duct in the AFT and Bulk

cargo compartments

1 Remove the sensing elements between Frame 55 thru Frame 83

Refer to Fig. A-GBFAA Sheet 01 thru Fig. A-GBFAA Sheet 03

Remove:

FIN 27HF

1 Sensing Element 35609-2-255 Item (562)

FIN 28HF

1 Sensing Element 35593-2-255 Item (564)

FIN 29HF

1 Sensing Element 35593-2-255 Item (566)

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 341

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SERVICE BULLETIN

FIN 30HF

1 Sensing Element 35609-2-255 Item (563)

FIN 31HF

1 Sensing Element 35609-2-255 Item (570)

FIN 32HF

1 Sensing Element 35609-2-255 Item (572)

attached with:

6 Nut Item (612) Retain

5 Flange Item (592) Discard

15 Sleeve Item (602) Discard

15 Clamp Item (357) Discard

8 Screw Item (408) Retain

8 Spacer Item (609) Discard

16 Clip Nut Item (399) Retain

16 Screw Item (601) Retain

2 Remove the connector of the sensing element at Frame 80/82

Refer to Fig. A-GBFAA Sheet 01 and Fig. A-GBFAA Sheet 03

Remove:

1 Connector Item (355) Discard

3 Washer Item (596) Discard

(29) Subtask 364033-831-212-001 - Drill an additional hole for the dual loop overheat

leak detection in the sheet metal pressure bulkhead

Manpower Resources

Manhours 0.75

Minimum number of person 1

Subtask elapsed time 0.75

Skills AIRFRAME

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 342

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@A340

SERVICE BULLETIN

References

Fig. A-GBMAA

Hole Location and Dimensions for the

sensing element Installation in the Sheet

Metal Pressure Bulkhead

Sheet 01

(a) Drill the hole for the dual loop overheat leak detection in the pressure bulkhead

For dimensions refer to Fig. A-GBMAA Sheet 01

1 Drill the additional sensing element hole into the pressure bulkhead Frame

80/82 with a diameter of 13.5mm (0.53in.)

(30) Subtask 364033-831-207-001 - Install the sensing elements in the AFT and Bulk

cargo compartments

Work Zones and Access Panels

Zone Access/Work location

From 160 Work location Frame 55

To 310 Work location Frame 83

Manpower Resources

Manhours 11.25

Minimum number of person 1

Subtask elapsed time 11.25

Skills ELECTRICAL

Material necessary to do the job

Kit 364033D10R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

57 D3627006026600 1 PLACARD

355 NSA5549-00 1 CONNECTR

356 F3627011520400 1 PLACARD

357 NSA5543-00 22 CLAMP

562 35602-2-255 2 ELEMENT

563 35600-2-255 2 SNSGELEM

564 35586-2-255 2 ELEMENT

566 35594-2-255 2 SNSGELEM

570 35604-2-255 2 SNSGELEM

572 35597-2-255 1 SNSGELEM

574 35599-3-255 1 ELEMENT

591 F3627011520600 1 PLACARD

592 NSA5546-00 6 ANGLE

593 F3627011522200 1 PLACARD

594 F3627011520800 2 PLACARD

596 A2117050220000 1 RING

597 NAS1149C0832R 1 WASHER

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 343

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SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

602 NSA5539S 152 SLEEVE

604 NAS1149C0863R 1 WASHER

606 F3627011520200 2 PLACARD

607 NAS1919C04S02U 12 RIVET

609 NSA5527-03-01 1 SPACER

610 NSA5538-00 2 CLAMP

611 F3627011521000 1 PLACARD

612 NSA5542-00 6 NUT

805 NAS1802-3-13 1 SCREW

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Lockwire 0.6 Mm 19-018 As required

References

Aircraft Maintenance Manual (AMM) Task 36-22-17-400-801

Fig. A-GBGAA

Installation of the Sensing Elements in

the Bulk and AFT Cargo Compartments

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

Fig. A-GBNAA

Tolerances for the Waviness and Bend

in the Electrical Wiring

Sheet 01

Sheet 02

(a) Install the sensing elements in the AFT and Bulk cargo compartments

Refer to AMM Task 36-22-17-400-801

1 For the installation of the sensing elements install the connection flanges

Refer to Fig. A-GBGAA Sheet 01 thru Fig. A-GBGAA Sheet 08

Put the angles, Item 592, in position within the given tolerance area, transfer

drill the rivet holes to the duct-brackets with the diameter between 3.28 mm

and 3.35 mm (0.129 in and 0.132 in) and install:

6 Angle NSA5546-00 Item 592

with:

12 Rivet-Blind NAS1919C04S02U Item 607

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 344

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2 Install the sensing elements between Frame 55 thru Frame 83

Refer to Fig. A-GBGAA Sheet 01 thru Fig. A-GBGAA Sheet 08

For the tolerances for waviness and bend in wires, refer to Fig. A-GBNAA

Sheet 01 thru Fig. A-GBNAA Sheet 02.

NOTE: The length compensation of the sensing elements must be

done at the couplings or retainer rings.

NOTE: The sensing elements must be installed in front of the

ventilation holes.

Install:

2 Sensing Element 35602-2-255 Item 562

2 Sensing Element 35600-2-255 Item 563

2 Sensing Element 35586-2-255 Item 564

2 Sensing Element 35594-2-255 Item 566

2 Sensing Element 35604-2-255 Item 570

1 Sensing Element 35597-2-255 Item 572

1 Sensing Element 35599-3-255 Item 574

with:

1 Connector NSA5549-00 Item 355

22 Clamp NSA5543-00 Item 357

16 Clip Nut Item (399) Retained at

removal

6 Screw Item (408) Retained at

removal

1 Ring-Sealing A2117050220000 Item 596

1 Washer NAS1149C0832R Item 597

16 Screw Item (601) Retained at

removal

152 Sleeve-Protective NSA5539S Item 602

1 Washer NAS1149C0863R Item 604

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 345

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SERVICE BULLETIN

1 Spacer NSA5527-03-01 Item 609

2 Clamp NSA5538-00 Item 610

6 Nut NSA5542-00 Item 612

6 Nut Item (612) Retained at

removal

1 Screw NAS1802-3-13 Item 805

NOTE: Secure the nuts, Item 612/(612), with lockwire:

Lockwire 0.6 Mm 19-018 As required

3 Install the identification placards of the sensing-elements between Frame 55

thru Frame 83

Refer to Fig. A-GBGAA Sheet 01 thru Fig. A-GBGAA Sheet 07

Install:

1 Placard F3627011520400 Item 356

1 Placard F3627011520600 Item 591

2 Placard F3627011520800 Item 594

1 Placard F3627011522200 Item 593

1 Placard F3627011521000 Item 611

2 Placard F3627011520200 Item 606

1 Placard D3627006026600 Item 57

(31) Subtask 364033-410-003-001 - If removed, install the ducts between FR39 and

FR40.

Work Zones and Access Panels

Zone Access/Work location

190

Manpower Resources

Manhours 2.00

Minimum number of person 1

Subtask elapsed time 2.00

Skills AIRFRAME

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 346

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@A340

SERVICE BULLETIN

References

Fig. A-FBPAA

Removal/Installation of the Ducts

Between FR39 and FR40 for Access

Sheet 01

(a) Install :

Fig. A-FBPAA

(Refer to AMM Task 21-20-00-410-801)

1 Duct assy Item (125) Retained at

removal

1 Duct assy Item (126) Retained at

removal

1 Duct assy Item (127) Retained at

removal

(32) Subtask 364033-831-208-002 - Remove the sensing elements in the rear fuselage

Work Zones and Access Panels

Zone Access/Work location

310 Work location from Frame 80 to Frame 95

Manpower Resources

Manhours 2.75

Minimum number of person 1

Subtask elapsed time 2.75

Skills ELECTRICAL

References

Fig. A-GBHAC

Removal of the Sensing Elements in the

Rear Fuselage Section

Sheet 01

Sheet 02

Sheet 03

Sheet 04

(a) Remove the sensing elements in the rear fuselage

1 Remove the sensing elements between Frame 80/82 thru Frame 95

Refer to Fig. A-GBHAC Sheet 01 thru Fig. A-GBHAC Sheet 04

Remove:

FIN 34HF

1 Sensing Element 35301-75 Item (361) Discard

FIN 139HF

1 Sensing Element 35558-2-310 Item (362) Discard

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 347

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SERVICE BULLETIN

FIN 140HF

1 Sensing Element 35636-2-310 Item (365) Discard

FIN 33HF

1 Sensing Element 35660-2-310 Item (370) Discard

attached with:

3 Screw Item (601) Discard

33 Screw Item (601) Retain

47 Sleeve Item (602) Discard

1 Screw Item (603) Retain

4 Screw Item (620) Retain

5 Spacer Item (609) Retain

40 Clamp Item (357) Discard

37 Nut-Clip Item (399) Retain

3 Flange Item (59) Discard

3 Nut Item (612) Retain

2 Clamp Item (621) Discard

2 Remove the connector of the sensing element at Frame 80/82

Refer to Fig. A-GBHAC Sheet 01 thru Fig. A-GBHAC Sheet 04

Remove:

1 Connector Item (355) Discard

1 Washer Item (596) Discard

1 Washer Item (604) Discard

(33) Subtask 364033-831-209-002 - Install the sensing elements in the rear fuselage

Work Zones and Access Panels

Zone Access/Work location

310 Work location from Frame 80 to Frame 95

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 348

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SERVICE BULLETIN

Manpower Resources

Manhours 5.75

Minimum number of person 1

Subtask elapsed time 5.75

Skills ELECTRICAL

Material necessary to do the job

Kit 364033D14R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

59 NSA5545-00 3 ANGLE

313 NAS1801-3-19 2 SCREW

314 NAS1801-3-8 2 SCREW

355 NSA5549-00 1 CONNECTR

357 NSA5543-00 37 CLAMP

360 35301-74 1 CABLE

361 35301-75 1 CABLE

362 35563-2-255 1 ELEMENT

363 35566-2-255 1 ELEMENT

365 35616-2-255 2 ELEMENT

369 35641-3-255 1 ELEMENT

370 35642-2-255 1 ELEMENT

372 AS21919WCH04 12 CLAMP

373 AS21919WCH10 2 CLAMP

374 F3617052620200 1 PLACARD

392 F3627011521400 1 PLACARD

393 F3627011521600 2 PLACARD

394 F3627011521800 2 PLACARD

397 NSA5527-03-04 2 SPACER

416 NAS1801-3-9 5 SCREW

496 NSA5527-03-08D 1 SPACER

591 F3617052620000 1 PLACARD

596 A2117050220000 1 RING

597 NAS1149C0832R 1 WASHER

602 NSA5539S 94 SLEEVE

604 NAS1149C0863R 1 WASHER

607 NAS1919C04S02U 6 RIVET

608 D3627006026800 1 PLACARD

609 NSA5527-03-01 3 SPACER

610 NSA5538-00 2 CLAMP

612 NSA5542-00 3 NUT

640 MS21042-3 5 NUT

682 NAS1149D0332K 7 WASHER

805 NAS1802-3-13 2 SCREW

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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SERVICE BULLETIN

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Lockwire 0.6 Mm 19-018 As required

References

Fig. A-GBJAC

Installation of the Sensing Elements in

the Rear Fuselage Section

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

(a) Install the sensing elements in the rear fuselage

1 For the installation of the sensing elements install the connection flanges

Refer to Fig. A-GBJAC Sheet 01 thru Fig. A-GBJAC Sheet 08

Install:

3 Connection Flanges NSA5545-00 Item 59

with:

6 Rivet-Blind NAS1919C04S02U Item 607

2 Install the sensing elements between Frame 80/82 thru Frame 95

Refer to Fig. A-GBJAC Sheet 01 thru Fig. A-GBJAC Sheet 08

NOTE: The length compensation of the sensing elements must be

done at the couplings or retainer rings.

NOTE: The sensing elements must be installed in front of the

ventilation holes.

Install:

FIN 361HF

1 Cable-Electrical

Interconnecting

35301-74 Item 360

FIN 34HF

1 Cable-Electrical

Interconnecting

35301-75 Item 361

FIN 139HF

1 Sensing Element 35563-2-255 Item 362

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 350

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SERVICE BULLETIN

FIN 359HF

1 Sensing Element 35566-2-255 Item 363

FIN 360HF

1 Sensing Element 35616-2-255 Item 365

FIN 140HF

1 Sensing Element 35616-2-255 Item 365

FIN 358HF

1 Sensing Element 35641-3-255 Item 369

FIN 33HF

1 Sensing Element 35642-2-255 Item 370

with:

1 Connector NSA5549-00 Item 355

1 Washer NAS1149C0832R Item 597

1 Ring-Sealing A2117050220000 Item 596

1 Washer NAS1149C0863R Item 604

attached with:

37 Nut-Clip Item (399) Retained at

removal

33 Screw Item (601) Retained at

removal

1 Screw Item (603) Retained at

removal

5 Spacer Item (609) Retained at

removal

3 Nut Item (612) Retained at

removal

4 Screw Item (620) Retained at

removal

2 Clamp Item (621) Retained at

removal

2 Screw NAS1801-3-19 Item 313

2 Screw NAS1801-3-8 Item 314

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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SERVICE BULLETIN

37 Clamp NSA5543-00 Item 357

12 Clamp AS21919WCH04 Item 372

2 Clamp AS21919WCH10 Item 373

2 Spacer NSA5527-03-04 Item 397

5 Screw NAS1801-3-9 Item 416

1 Spacer NSA5527-03-08D Item 496

94 Sleeve-Protective NSA5539S Item 602

3 Spacer NSA5527-03-01 Item 609

2 Clamp NSA5538-00 Item 610

3 Nut NSA5542-00 Item 612

5 Nut MS21042-3 Item 640

7 Washer NAS1149D0332K Item 682

2 Screw NAS1802-3-13 Item 805

NOTE: Secure the nuts, Item 612/(612), with lockwire:

Lockwire 0.6 Mm 19-018 As required

3 Install the identification placards of the sensing-elements between Frame

80/82 thru Frame 95

Refer to Fig. A-GBJAC Sheet 01 thru Fig. A-GBJAC Sheet 08

Install:

1 Placard F3617052620200 Item 374

1 Placard F3627011521400 Item 392

2 Placard F3627011521600 Item 393

2 Placard F3627011521800 Item 394

1 Placard F3617052620000 Item 591

1 Placard D3627006026800 Item 608

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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SERVICE BULLETIN

(34) Subtask 364033-831-210-002 - Install the sleeves at the APU Bleed Air Duct

Work Zones and Access Panels

Zone Access/Work location

310 Work location from Frame 80 to Frame 95

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills ELECTRICAL

Material necessary to do the job

Kit 364033D17R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

377 F3617062400400 1 SLEEVE

380 F3617062401600 1 SLEEVE

382 F3617062402200 1 SLEEVE

383 F3617062403200 1 SLEEVE

384 F3617062403400 1 SLEEVE

385 F3617062403600 1 SLEEVE

386 F3617062403800 1 SLEEVE

387 F3617062404000 1 SLEEVE

602 NSA5539S 6 SLEEVE

References

Fig. A-GBKAC

Installation of the Sleeves at the APU

Bleed Air Duct

Sheet 01

(a) Install the sleeves at the APU Bleed Air Duct between Frame 80/82 thru Frame 95

Refer to Fig. A-GBKAC Sheet 01

install the sleeves and close them with the adhesive strips:

1 Sleeve Assy F3617062400400 Item 377

1 Sleeve Assy F3617062401600 Item 380

1 Sleeve Assy F3617062402200 Item 382

1 Sleeve F3617062403200 Item 383

1 Sleeve F3617062403400 Item 384

1 Sleeve F3617062403600 Item 385

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 353

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SERVICE BULLETIN

1 Sleeve F3617062403800 Item 386

1 Sleeve F3617062404000 Item 387

Close the sleeves with:

6 Sleeve-Protective NSA5539S Item 602

NOTE: Make sure that the blowout apertures of the blankets are close to

(under) the sensing elements.

**CONF 004

(1) Subtask 364033-831-016-001 - Modify the Wiring between the Avionics

Compartment and the Cargo Compartment.

Work Zones and Access Panels

Zone Access/Work location

190

Manpower Resources

Manhours 2.00

Minimum number of person 2

Subtask elapsed time 2.00

Skills ELECTRICAL

Material necessary to do the job

Kit 364033A02R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

169 NSA935401-03 300 TIE

F9000095227895 BUNDLE

NSA935401-08 300 TIE

NSA935401-13 300 TIE

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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References

Fig. A-FBMAA

Installation of the New Harness 2SG

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

Sheet 09

Sheet 10

Sheet 11

Sheet 12

Sheet 13

Sheet 14

Sheet 15

Sheet 16

Sheet 17

Sheet 18

Sheet 19

Sheet 20

Sheet 21

Sheet 22

Fig. A-FCBAA

Modification of the Wiring between the

Cargo Compartment and the Avionics

Compartment

Sheet 01

Sheet 02

(a) As shown in Fig. A-FBMAA Sheet 01, install the wire, using spares conduits

between Frame 37 and Frame 53.2, as shown on the wiring diagram, Fig. AFCBAA Sheet 01 and as given in the Hook-up Chart line :

- 1 (Refer to Fig. A-FCBAA Sheet 02) supplied in :

Bundle F9000095227895

NOTE: The spares conduits is divided in two parts. The first parts go away

from Frame 40 to Frame 47 and the second parts go away from

Frame 48 to Frame 53.2

(b) Attach the wires with :

300 Tie-Cable NSA935401-03 Item 169

300 Tie-Cable NSA935401-08

300 Tie-Cable NSA935401-13

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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SERVICE BULLETIN

(2) Subtask 364033-831-017-001 - Modify the Wiring in the Main rack 800VU.

Work Zones and Access Panels

Zone Access/Work location

120 Work location Electrical panel 800VU

Manpower Resources

Manhours 4.00

Minimum number of person 2

Subtask elapsed time 2.00

Skills ELECTRICAL

Material necessary to do the job

Kit 364033A02R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

169 NSA935401-03 50 TIE

F9000095227895 BUNDLE

NSA935401-06 50 TIE

NSA935401-13 50 TIE

References

Aircraft Maintenance Manual (AMM) Task 36-11-34-000-802

Task 36-11-34-400-802

Fig. A-FCAAA

Modification of the Wiring in the Main

Rack 800VU

Sheet 01

Sheet 02

Sheet 03

Sheet 04

(a) Remove and retain the BMC (FIN 1HA1, 1HA2, 1HA3 and 1HA4) (Refer to AMM

Task 36-11-34-000-802).

(b) Remove the wires as shown on the wiring diagram Fig. A-FCAAA Sheet 01, and as

given in the Hook-up Chart lines :

- 1 thru 5 (Refer to Fig. A-FCAAA Sheet 04).

(c) Install the wires as shown on the wiring diagrams, Fig. A-FCAAA Sheet 02 and Fig.

A-FCAAA Sheet 03 and as given in the Hook-up Chart lines :

- 9 thru 19 (Refer to Fig. A-FCAAA Sheet 04) supplied in :

Bundle F9000095227895

(d) Attach the wires with :

50 Tie-Cable NSA935401-03 Item 169

50 Tie-Cable NSA935401-06

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 356

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SERVICE BULLETIN

50 Tie-Cable NSA935401-13

(e) Install the BMC (FIN 1HA1, 1HA2, 1HA3 and 1HA4) (Refer to AMM Task

36-11-34-400-802).

(3) Subtask 364033-831-001-001 - Remove the sensing elements and the supports

between FR39 and FR44.

Work Zones and Access Panels

Zone Access/Work location

190 Work location from Frame 39 to Frame 44

Manpower Resources

Manhours 4.00

Minimum number of person 1

Subtask elapsed time 4.00

Skills AIRFRAME

References

Aircraft Maintenance Manual (AMM) Task 36-22-17-000-801

Task 36-22-17-000-802

Fig. A-FBAAA

Removal of the Sensing Elements

between FR39 and FR55 on the LH side

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

(a) Remove :

Fig. A-FBAAA Sheet 01 Fig. A-FBAAA Sheet 02

(Refer to AMM Task 36-22-17-000-801 and AMM Task 36-22-17-000-802)

22 Screw Item (20) Discard

32 Washer Item (14) Discard

32 Clamp Item (86) Discard

32 Sleeve Item (13) Discard

5 Screw Item (91) Discard

10 Spacer Item (16) Discard

5 Screw Item (21) Discard

2 Nut Item (15) Discard

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 357

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@A340

SERVICE BULLETIN

FIN 97HF

1 Sensing Element 35610-2-255 Item (1) Discard

FIN 98HF

1 Sensing Element 35624-2-255 Item (2) Discard

4 Rivet Item (11) Discard

2 Support Item (10) Discard

(4) Subtask 364033-831-002-001 - Remove the sensing elements and the supports

between FR44 and FR51.

Work Zones and Access Panels

Zone Access/Work location

190 Work location from Frame 44 to Frame 51

Manpower Resources

Manhours 4.00

Minimum number of person 1

Subtask elapsed time 4.00

Skills AIRFRAME

References

Aircraft Maintenance Manual (AMM) Task 36-22-17-000-801

Fig. A-FBAAA

Removal of the Sensing Elements

between FR39 and FR55 on the LH side

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

(a) Remove :

Fig. A-FBAAA Sheet 01 Fig. A-FBAAA Sheet 03

(Refer to AMM Task 36-22-17-000-801)

18 Screw Item (21) Discard

30 Washer Item (14) Discard

30 Clamp Item (86) Discard

30 Sleeve Item (13) Discard

18 Spacer Item (16) Discard

12 Screw Item (20) Discard

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 358

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@A340

SERVICE BULLETIN

2 Nut Item (15) Discard

FIN 99HF

1 Sensing Element 35612-2-255 Item (3) Discard

FIN 100HF

1 Sensing Element 35605-2-255 Item (6) Discard

4 Rivet Item (11) Discard

2 Support Item (10) Discard

(5) Subtask 364033-831-003-001 - Remove the sensing elements and the supports

between FR51 and FR53.6.

Work Zones and Access Panels

Zone Access/Work location

190 Work location from Frame 51 to Frame 53.6

Manpower Resources

Manhours 4.00

Minimum number of person 1

Subtask elapsed time 4.00

Skills AIRFRAME

References

Aircraft Maintenance Manual (AMM) Task 36-22-17-000-801

Task 36-22-17-000-802

Fig. A-FBAAA

Removal of the Sensing Elements

between FR39 and FR55 on the LH side

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

(a) Remove :

Fig. A-FBAAA Sheet 01 Fig. A-FBAAA Sheet 04

(Refer to AMM Task 36-22-17-000-801 and AMM Task 36-22-17-000-802)

18 Screw Item (21) Discard

37 Washer Item (14) Discard

37 Clamp Item (86) Discard

37 Sleeve Item (13) Discard

23 Spacer Item (16) Discard

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 359

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SERVICE BULLETIN

16 Screw Item (20) Discard

1 Screw Item (93) Discard

1 Spacer Item (18) Discard

2 Screw Item (91) Discard

3 Nut Item (15) Discard

FIN 101HF

1 Sensing Element 35603-2-255 Item (4) Discard

FIN 102HF

1 Sensing Element 35600-2-255 Item (5) Discard

FIN 23HF

1 Sensing Element 35571-2-255 Item (7) Discard

6 Rivet Item (11) Discard

3 Support Item (10) Discard

(6) Subtask 364033-831-004-001 - Remove the sensing elements and the supports

between FR53.6 and FR55.

Work Zones and Access Panels

Zone Access/Work location

190 Work location from Frame 53.6 to Frame 55

Manpower Resources

Manhours 4.00

Minimum number of person 1

Subtask elapsed time 4.00

Skills AIRFRAME

References

Aircraft Maintenance Manual (AMM) Task 36-22-17-000-801

Fig. A-FBAAA

Removal of the Sensing Elements

between FR39 and FR55 on the LH side

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

(a) Remove :

Fig. A-FBAAA Sheet 01 Fig. A-FBAAA Sheet 05

(Refer to AMM Task 36-22-17-000-801)

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 360

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SERVICE BULLETIN

19 Screw Item (20) Discard

27 Washer Item (14) Discard

27 Clamp Item (86) Discard

27 Sleeve Item (13) Discard

4 Screw Item (91) Discard

12 Spacer Item (16) Discard

4 Screw Item (21) Discard

2 Nut Item (15) Discard

FIN 24HF

1 Sensing Element 35580-2-255 Item (8) Discard

FIN 25HF

1 Sensing Element 35611-3-255 Item (9) Discard

2 Rivet Item (11) Discard

1 Support Item (10) Discard

(7) Subtask 364033-010-002-001 - If necessary, remove the ducts between FR53.5 and

FR53.6 for access.

Work Zones and Access Panels

Zone Access/Work location

150 Work location from Frame 53.5 to Frame 53.6

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills AIRFRAME

References

Aircraft Maintenance Manual (AMM) Task 36-12-41-000-801

Fig. A-FBBAA

Removal/Installation of the Ducts

between FR53.6 and FR53.7 on the LH

side (for Access)

Sheet 01

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 361

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SERVICE BULLETIN

(a) Remove :

Fig. A-FBBAA

(Refer to AMM Task 36-12-41-000-801)

1 Duct assy Item (112) Retain

1 Duct assy Item (112) Retain

1 Duct assy Item (114) Retain

(8) Subtask 364033-831-005-001 - Drill a new hole in the structure between FR53.5 and

FR53.6.

Work Zones and Access Panels

Zone Access/Work location

150 Work location from Frame 53.5 to Frame 53.6

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills AIRFRAME

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Chemical Conversion

Coating Yellow Aluminum

13-002 As required

Anti-Corrosion Primer

(polyurethane)

16-001 As required

Polyurethane Finnish Paint 16-018 As required

References

Fig. A-FBCAA

Drilling of a New Hole in the Structure

between FR53.5 and FR53.6 on the LH

side and Installation of Sensing

Elements

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

(a) Drill one hole on the structure between FR53.5 and FR53.6 to a diameter

comprised between 13.5mm (0.531in.) Min. and 13.7mm (0.539 in.) Max. as shown

on Fig. A-FBCAA.

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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SERVICE BULLETIN

(b) Do a spotfacing on the structure between FR53.5 and 53.6 to a diameter of 24mm

(0.944 in.) with a radius of 2mm (0.078in.)

NOTE: Be careful at the depth : 2mm (0.078 in.) Min. and 3mm (0.118 in.)

Max.

(c) Protect the hole and the spotfacing with :

Chemical

Conversion Coating

Yellow Aluminum

13-002 As required

Anti-Corrosion

Primer

(polyurethane)

16-001 As required

Polyurethane

Finnish Paint

16-018 As required

(9) Subtask 364033-831-006-001 - Install a new support for the routing of the sensing

elements between FR53.5 and FR53.6.

Work Zones and Access Panels

Zone Access/Work location

150 Work location from Frame 53.5 to Frame 53.6

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills NON SPECIFIC

Material necessary to do the job

Kit 364033A01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

96 F5392059300000 1 SUPPORT

97 ASNA2050DCJ3215 2 RIVET

Reidentified part set REIDA01

ITEM NEW PART N ̊ KEYWORD ITEM OLD PART N ̊ SEE

NOTES

F0041196200000 BLANKET F2581571700000

F2582261900000

F0041196300000 BLANKET F2581566600000

F0041196400000 BLANKET F2581666600000

F0041196500000 BLANKET F2581677800000

F0041196600000 BLANKET F2581677900000

F0041196700000 BLANKET F2582242300000

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 363

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@A340

SERVICE BULLETIN

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Adhesive Tape (insulation

Blanket Repair)

08-073 As required

Interfay Sealant 09-005A As required

Corrosion Inhibiting Fillet

Consistency

09-016B As required

References

Fig. A-FBFAA

Installation of a New Bracket between

FR53.5 and FR53.6

Sheet 01

Sheet 02

(a) Move the insulation blanket to get access to the modification area.

(b) Put the bracket Item 96 in position as shown on Fig. A-FBFAA.

(c) Drill two holes on the structure to a diameter comprised between 3.25mm (0.128in.)

and 3.35mm (0.132in.) to match the holes of the bracket Item 96.

Fig. A-FBFAA

(d) Cut the insulation blanket to permit the installation of the bracket Item 96.

NOTE: For the repair of the insulation blanket use :

Adhesive Tape

(insulation Blanket

Repair)

08-073 As required

(e) Re-identify the insulation blanket :

1 Blanket-Insulation F2581571700000

or

1 Blanket-Insulation F2582261900000

becomes

1 Blanket-Insulation F0041196200000

or

1 Blanket-Insulation F2581566600000

becomes

1 Blanket-Insulation F0041196300000

or

1 Blanket-Insulation F2581666600000

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 364

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becomes

1 Blanket-Insulation F0041196400000

or

1 Blanket-Insulation F2581677800000

becomes

1 Blanket-Insulation F0041196500000

or

1 Blanket-Insulation F2581677900000

becomes

1 Blanket-Insulation F0041196600000

or

1 Blanket-Insulation F2582242300000

becomes

1 Blanket-Insulation F0041196700000

(f) Install :

Fig. A-FBFAA

1 Support F5392059300000 Item 96

2 Rivet ASNA2050DCJ3215 Item 97

NOTE: To the interface of the new bracket and the structure, apply :

Interfay Sealant 09-005A As required

NOTE: Do a sealant bead around new parts with :

Corrosion Inhibiting

Fillet Consistency

09-016B As required

NOTE: Wet install the fasteners with :

Interfay Sealant 09-005A As required

(g) Install the insulation blanket.

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 365

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@A340

SERVICE BULLETIN

(10) Subtask 364033-410-001-001 - If removed, install the ducts between FR53.5 and

FR53.6.

Work Zones and Access Panels

Zone Access/Work location

150 Work location from Frame 53.5 to Frame 53.6

Manpower Resources

Manhours 2.00

Minimum number of person 1

Subtask elapsed time 2.00

Skills AIRFRAME

References

Aircraft Maintenance Manual (AMM) Task 36-12-41-400-801

Fig. A-FBBAA

Removal/Installation of the Ducts

between FR53.6 and FR53.7 on the LH

side (for Access)

Sheet 01

(a) Install :

(Refer to AMM Task 36-12-41-400-801)

1 Duct assy Item (112) Retained at

removal

1 Duct assy Item (112) Retained at

removal

1 Duct assy Item (114) Retained at

removal

(11) Subtask 364033-010-003-001 - If necessary, remove the ducts between FR43 and

FR45 for access.

Work Zones and Access Panels

Zone Access/Work location

190 Work location from Frame 43 to Frame 45

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 36-12-41-000-801

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 366

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SERVICE BULLETIN

References

Fig. A-FBDAA

Removal/Installation of the Ducts

between FR44 and FR47 on the LH side

(for Access)

Sheet 01

(a) Remove :

(Refer to AMM Task 36-12-41-000-801)

1 Duct assy Item (115) Retain

1 Duct assy Item (116) Retain

(12) Subtask 364033-831-007-001 - Replace the web assy and the half clamp assy at

FR44.

Work Zones and Access Panels

Zone Access/Work location

190 Work location Frame 44

Manpower Resources

Manhours 3.00

Minimum number of person 1

Subtask elapsed time 3.00

Skills AIRFRAME

Material necessary to do the job

Kit 364033A01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

117 F5331591000200 1 WEB

118 F5331583500200 1 CLAMP

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Corrosion Inhibiting Fillet

Consistency

09-016B As required

Low Adhesion Polysulfide

Sealant

09-019B As required

References

Fig. A-FBEAA

Replacement of the Web Assy at FR44

on the LH side

Sheet 01

Sheet 02

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 367

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@A340

SERVICE BULLETIN

(a) Remove :

Fig. A-FBEAA

17 Screw Item (119) Retain

17 Washer Item (124) Retain

1 Strip cover assy Item (122) Retain

2 Screw Item (120) Retain

1 Half clamp assy F5331583500000 Item (118) Discard

1 Half clamp assy Item (121) Retain

1 Bracket Item (123) Retain

1 Web Assy F5331591000000 Item (117) Discard

NOTE: It is not necessary to remove completely the bracket Item (123).

(b) Install :

Fig. A-FBEAA

1 Web Assy F5331591000200 Item 117

1 Bracket Item (123) Retained at

removal

1 Half clamp assy Item (121) Retained at

removal

1 Half clamp assy F5331583500200 Item 118

2 Screw Item (120) Retained at

removal

1 Strip cover assy Item (122) Retained at

removal

17 Washer Item (124) Retained at

removal

17 Screw Item (119) Retained at

removal

NOTE: Install the new web assy with :

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 368

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@A340

SERVICE BULLETIN

Corrosion Inhibiting

Fillet Consistency

09-016B As required

and

Low Adhesion

Polysulfide Sealant

09-019B As required

(13) Subtask 364033-831-008-001 - Install the new brackets for the routing of the

sensing elements at FR44.

Work Zones and Access Panels

Zone Access/Work location

190 Work location Frame 44

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills AIRFRAME

Material necessary to do the job

Kit 364033A01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

97 ASNA2050DCJ3215 2 RIVET

98 F0041178800000 1 SUPPORT

99 F0041178800100 1 SUPPORT

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Interfay Sealant 09-005A As required

Corrosion Inhibiting Fillet

Consistency

09-016B As required

References

Fig. A-FBGAA

Installation of Two New Brackets at

FR44

Sheet 01

Sheet 02

(a) Put the brackets Item 98 and 99 in position as shown on Fig. A-FBGAA.

(b) Drill two holes to a diameter comprised between 3.25mm (0.128in.) and 3.35mm

(0.132in.) as shown on Fig. A-FBGAA.

(c) Install :

1 Support F0041178800000 Item 98

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 369

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@A340

SERVICE BULLETIN

1 Support F0041178800100 Item 99

2 Rivet ASNA2050DCJ3215 Item 97

NOTE: To the interface of the new bracket and the structure apply :

Interfay Sealant 09-005A As required

NOTE: Do a sealant bead around new parts with :

Corrosion Inhibiting

Fillet Consistency

09-016B As required

NOTE: Wet install the fasteners with :

Interfay Sealant 09-005A As required

(14) Subtask 364033-410-002-001 - If removed, install the ducts between FR43 and

FR45.

Work Zones and Access Panels

Zone Access/Work location

190 Work location from Frame 43 to Frame 45

Manpower Resources

Manhours 2.00

Minimum number of person 1

Subtask elapsed time 2.00

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 36-12-41-400-801

Fig. A-FBDAA

Removal/Installation of the Ducts

between FR44 and FR47 on the LH side

(for Access)

Sheet 01

(a) Install :

(Refer to AMM Task 36-12-41-400-801)

1 Duct assy Item (115) Retained at

removal

1 Duct assy Item (116) Retained at

removal

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 370

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@A340

SERVICE BULLETIN

(15) Subtask 364033-831-009-001 - Install the sensing elements and the supports

between FR39 and FR44.

Work Zones and Access Panels

Zone Access/Work location

190 Work location from Frame 39 to Frame 44

Manpower Resources

Manhours 14.00

Minimum number of person 1

Subtask elapsed time 14.00

Skills AIRFRAME

Material necessary to do the job

Kit 364033A01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

10 NSA5543-00 30 CLAMP

11 ASNA0342T04-01 4 BOLT

13 NSA5539S 62 SLEEVE

14 ASNA2397-10L 34 WASHER

15 NSA5542-00 4 NUT

16 NSA5527-03-01 8 SPACER

18 NSA5527-03-11 6 SPACER

20 NAS6603-1 19 BOLT

21 NAS6603-9 8 BOLT

24 NAS6603-15 6 BOLT

29 NAS6603-2 2 BOLT

30 NSA5546-00 2 ANGLE

32 F1131031621700 2 PLACARD

33 F1131031623700 2 PLACARD

34 F1131031621800 1 PLACARD

35 F1131031623800 1 PLACARD

70 F3611548300000 1 SUPPORT

71 F3611548800000 1 SUPPORT

78 F3611549700000 1 SUPPORT

79 F3611549100000 1 SUPPORT

100 35606-2-255 1 SNSGELEM

101 35621-2-255 1 SNSGELEM

102 35620-2-255 1 SNSGELEM

113 35610-2-255 1 SNSGELEM

References

Fig. A-FBHAA

Installation of the New Sensing

Elements between FR39 and FR44 on

LH side

Sheet 01

Sheet 02

Sheet 03

Sheet 04

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 371

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SERVICE BULLETIN

(a) Install the sensing elements and the supports between FR39 and FR40.2.

1 Install the supports between FR39 and FR40 :

1 Angle NSA5546-00 Item 30

2 Rivet-Blind ASNA0342T04-01 Item 11

8 Clamp NSA5543-00 Item 10

6 Spacer NSA5527-03-01 Item 16

2 Spacer NSA5527-03-11 Item 18

8 Washer ASNA2397-10L Item 14

6 Bolt NAS6603-9 Item 21

2 Bolt NAS6603-15 Item 24

2 Install the supports between FR40 and FR40.2 :

1 Support F3611549100000 Item 79

1 Support F3611549700000 Item 78

5 Clamp NSA5543-00 Item 10

1 Spacer NSA5527-03-01 Item 16

8 Washer ASNA2397-10L Item 14

1 Bolt NAS6603-9 Item 21

6 Bolt NAS6603-1 Item 20

2 Bolt NAS6603-2 Item 29

1 Angle NSA5546-00 Item 30

2 Rivet-Blind ASNA0342T04-01 Item 11

3 Install the placards between FR39 and FR40.2 :

2 Placard F1131031621700 Item 32

2 Placard F1131031623700 Item 33

1 Placard F1131031621800 Item 34

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 372

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SERVICE BULLETIN

1 Placard F1131031623800 Item 35

4 Install the sensing elements between FR39 and FR40.2 :

FIN 97HF

1 Sensing Element 35606-2-255 Item 100

FIN 302HF

1 Sensing Element 35610-2-255 Item 113

28 Sleeve-Protective NSA5539S Item 13

4 Nut NSA5542-00 Item 15

NOTE: Secure the nuts Item 15 with wire-lock MS20995C32 Item 27.

(b) Install the sensing elements and the supports between FR40.2 and FR44.

1 Install the supports between FR40.2 and FR44 :

1 Support F3611548300000 Item 70

1 Support F3611548800000 Item 71

17 Clamp NSA5543-00 Item 10

4 Spacer NSA5527-03-11 Item 18

1 Spacer NSA5527-03-01 Item 16

18 Washer ASNA2397-10L Item 14

13 Bolt NAS6603-1 Item 20

1 Bolt NAS6603-9 Item 21

4 Bolt NAS6603-15 Item 24

2 Install the sensing elements between FR40.2 and FR44 :

FIN 98HF

1 Sensing Element 35620-2-255 Item 102

FIN 303HF

1 Sensing Element 35621-2-255 Item 101

34 Sleeve-Protective NSA5539S Item 13

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 373

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SERVICE BULLETIN

(16) Subtask 364033-831-010-001 - Install the sensing elements and the supports

between FR44 and FR50.

Work Zones and Access Panels

Zone Access/Work location

190 Work location from Frame 44 to Frame 50

Manpower Resources

Manhours 14.00

Minimum number of person 1

Subtask elapsed time 14.00

Skills AIRFRAME

Material necessary to do the job

Kit 364033A01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

10 NSA5543-00 29 CLAMP

11 ASNA0342T04-01 4 BOLT

13 NSA5539S 58 SLEEVE

14 ASNA2397-10L 35 WASHER

15 NSA5542-00 8 NUT

16 NSA5527-03-01 11 SPACER

17 NSA5527-03-10 1 SPACER

18 NSA5527-03-11 3 SPACER

19 NAS6603-24 2 BOLT

20 NAS6603-1 14 BOLT

21 NAS6603-9 9 BOLT

23 NAS6603-16 1 BOLT

26 NAS6603-32 1 BOLT

29 NAS6603-2 8 BOLT

30 NSA5546-00 2 ANGLE

34 F1131031621800 1 PLACARD

35 F1131031623800 1 PLACARD

36 F1131031623900 2 PLACARD

37 F1131031621900 2 PLACARD

38 F1131031624000 2 PLACARD

39 F1131031622000 2 PLACARD

40 F1131031622100 1 PLACARD

41 F1131031624100 1 PLACARD

79 F3611549100000 4 SUPPORT

80 F3611549500000 1 SUPPORT

81 F3611549600000 1 SUPPORT

103 35618-2-255 2 SNSGELEM

105 35598-2-255 1 SNSGELEM

114 35597-2-255 1 SNSGELEM

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 374

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@A340

SERVICE BULLETIN

References

Fig. A-FBJAA

Installation of the New Sensing

Elements between FR44 and FR50 on

LH side

Sheet 01

Sheet 02

Sheet 03

Sheet 04

(a) Install the sensing elements and the supports between FR44 and FR46.

1 Install the supports between FR44 and FR46 :

1 Support F3611549600000 Item 81

17 Clamp NSA5543-00 Item 10

9 Spacer NSA5527-03-01 Item 16

3 Spacer NSA5527-03-11 Item 18

21 Washer ASNA2397-10L Item 14

2 Bolt NAS6603-24 Item 19

5 Bolt NAS6603-1 Item 20

7 Bolt NAS6603-9 Item 21

1 Bolt NAS6603-16 Item 23

2 Bolt NAS6603-2 Item 29

2 Install the placards at FR44 :

1 Placard F1131031621800 Item 34

1 Placard F1131031623800 Item 35

1 Placard F1131031623900 Item 36

1 Placard F1131031621900 Item 37

3 Install the sensing elements between FR44 and FR46 :

FIN 99HF

1 Sensing Element 35618-2-255 Item 103

FIN 304HF

1 Sensing Element 35618-2-255 Item 103

34 Sleeve-Protective NSA5539S Item 13

4 Nut NSA5542-00 Item 15

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 375

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@A340

SERVICE BULLETIN

(b) Install the sensing elements and the supports between FR46 and FR50.

1 Install the supports between FR46 and FR50 :

2 Angle NSA5546-00 Item 30

4 Rivet-Blind ASNA0342T04-01 Item 11

1 Support F3611549500000 Item 80

4 Support F3611549100000 Item 79

12 Clamp NSA5543-00 Item 10

2 Spacer NSA5527-03-01 Item 16

1 Spacer NSA5527-03-10 Item 17

14 Washer ASNA2397-10L Item 14

9 Bolt NAS6603-1 Item 20

2 Bolt NAS6603-9 Item 21

1 Bolt NAS6603-32 Item 26

6 Bolt NAS6603-2 Item 29

2 Install the placards between FR46 and FR50 :

1 Placard F1131031623900 Item 36

1 Placard F1131031621900 Item 37

2 Placard F1131031624000 Item 38

2 Placard F1131031622000 Item 39

1 Placard F1131031622100 Item 40

1 Placard F1131031624100 Item 41

3 Install the sensing elements between FR46 and FR50 :

FIN 100HF

1 Sensing Element 35597-2-255 Item 114

FIN 305HF

1 Sensing Element 35598-2-255 Item 105

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 376

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SERVICE BULLETIN

24 Sleeve-Protective NSA5539S Item 13

4 Nut NSA5542-00 Item 15

NOTE: Secure the nuts Item 15 with wire-lock MS20995C32 Item 27.

(17) Subtask 364033-831-011-001 - Install the sensing elements and the supports

between FR50 and FR53.6.

Work Zones and Access Panels

Zone Access/Work location

190 Work location from Frame 50 to Frame 53.6

Manpower Resources

Manhours 21.00

Minimum number of person 1

Subtask elapsed time 21.00

Skills AIRFRAME

Material necessary to do the job

Kit 364033A01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

10 NSA5543-00 37 CLAMP

11 ASNA0342T04-01 6 BOLT

13 NSA5539S 74 SLEEVE

14 ASNA2397-10L 51 WASHER

15 NSA5542-00 6 NUT

16 NSA5527-03-01 16 SPACER

18 NSA5527-03-11 1 SPACER

20 NAS6603-1 23 BOLT

21 NAS6603-9 16 BOLT

22 NSA5527-03-15 1 SPACER

24 NAS6603-15 1 BOLT

25 NSA5545-00 1 ANGLE

28 NAS6603-12 1 BOLT

29 NAS6603-2 10 BOLT

30 NSA5546-00 2 ANGLE

40 F1131031622100 1 PLACARD

41 F1131031624100 1 PLACARD

42 F1131031622200 2 PLACARD

43 F1131031624200 2 PLACARD

44 F1131031620400 2 PLACARD

45 F1131031624300 2 PLACARD

70 F3611548300000 1 SUPPORT

72 F3611548700000 1 SUPPORT

73 F3611548500000 1 SUPPORT

74 F3611548900000 1 SUPPORT

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 377

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@A340

SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

75 F3611548400000 1 SUPPORT

76 F3611548200000 1 SUPPORT

77 F3611548620000 1 SUPPORT

79 F3611549100000 3 SUPPORT

82 F3611549400000 1 SUPPORT

83 F3611549800000 1 SUPPORT

84 F3611549300000 1 SUPPORT

104 35567-3-255 1 SNSGELEM

106 35595-2-255 3 SNSGELEM

107 35596-2-255 1 SNSGELEM

108 35568-4-255 1 SNSGELEM

References

Fig. A-FBKAA

Installation of the New Sensing

Elements between FR50 and FR53.6 on

LH side

Sheet 01

Sheet 02

Sheet 03

Sheet 04

(a) Install the sensing elements and the supports between FR50 and FR53.2.

1 Install the supports between FR50 and FR53.2 :

1 Support F3611548700000 Item 72

1 Support F3611548400000 Item 75

1 Support F3611549400000 Item 82

1 Angle NSA5546-00 Item 30

2 Rivet-Blind ASNA0342T04-01 Item 11

13 Clamp NSA5543-00 Item 10

7 Spacer NSA5527-03-01 Item 16

16 Washer ASNA2397-10L Item 14

9 Bolt NAS6603-1 Item 20

7 Bolt NAS6603-9 Item 21

2 Install the placards between FR50 and FR53.2 :

1 Placard F1131031622100 Item 40

1 Placard F1131031624100 Item 41

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 378

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@A340

SERVICE BULLETIN

1 Placard F1131031622200 Item 42

1 Placard F1131031624200 Item 43

3 Install the sensing elements between FR50 and FR53.2 :

FIN 101HF

1 Sensing Element 35595-2-255 Item 106

FIN 306HF

1 Sensing Element 35595-2-255 Item 106

26 Sleeve-Protective NSA5539S Item 13

2 Nut NSA5542-00 Item 15

NOTE: Secure the nuts Item 15 with wire-lock MS20995C32 Item 27.

(b) Install the sensing elements and the supports between FR53.2 and FR53.6.

1 Install the supports between FR53.2 and FR53.6 :

1 Support F3611548300000 Item 70

1 Support F3611548500000 Item 73

1 Support F3611548900000 Item 74

1 Support F3611548200000 Item 76

1 Support F3611548620000 Item 77

3 Support F3611549100000 Item 79

1 Support F3611549800000 Item 83

1 Support F3611549300000 Item 84

1 Angle NSA5545-00 Item 25

1 Angle NSA5546-00 Item 30

4 Rivet-Blind ASNA0342T04-01 Item 11

24 Clamp NSA5543-00 Item 10

9 Spacer NSA5527-03-01 Item 16

1 Spacer NSA5527-03-11 Item 18

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 379

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SERVICE BULLETIN

1 Spacer NSA5527-03-15 Item 22

35 Washer ASNA2397-10L Item 14

14 Bolt NAS6603-1 Item 20

9 Bolt NAS6603-9 Item 21

1 Bolt NAS6603-15 Item 24

1 Bolt NAS6603-12 Item 28

10 Bolt NAS6603-2 Item 29

2 Install the placards between FR53.2 and FR53.6 :

1 Placard F1131031622200 Item 42

1 Placard F1131031624200 Item 43

2 Placard F1131031620400 Item 44

2 Placard F1131031624300 Item 45

3 Install the sensing elements between FR53.2 and FR53.6 :

FIN 102HF

1 Sensing Element 35595-2-255 Item 106

FIN 307HF

1 Sensing Element 35596-2-255 Item 107

FIN 23HF

1 Sensing Element 35568-4-255 Item 108

FIN 308HF

1 Sensing Element 35567-3-255 Item 104

48 Sleeve-Protective NSA5539S Item 13

4 Nut NSA5542-00 Item 15

NOTE: Secure the nuts Item 15 with wire-lock MS20995C32 Item 27.

(18) Subtask 364033-831-012-001 - Install the sensing elements and the supports

between FR53.6 and FR55.

Work Zones and Access Panels

Zone Access/Work location

190 Work location from Frame 53.6 to Frame 55

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 380

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@A340

SERVICE BULLETIN

Manpower Resources

Manhours 14.00

Minimum number of person 1

Subtask elapsed time 14.00

Skills AIRFRAME

Material necessary to do the job

Kit 364033A01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

10 NSA5543-00 27 CLAMP

11 ASNA0342T04-01 2 BOLT

13 NSA5539S 55 SLEEVE

14 ASNA2397-10L 32 WASHER

15 NSA5542-00 2 NUT

16 NSA5527-03-01 6 SPACER

17 NSA5527-03-10 2 SPACER

18 NSA5527-03-11 5 SPACER

20 NAS6603-1 17 BOLT

21 NAS6603-9 1 BOLT

26 NAS6603-32 2 BOLT

29 NAS6603-2 2 BOLT

30 NSA5546-00 1 ANGLE

70 F3611548300000 1 SUPPORT

79 F3611549100000 1 SUPPORT

85 NSA5549-90 2 CONNECTR

86 NSA5538-00 3 CLAMP

87 NAS6603-17 5 BOLT

88 F1131031620500 1 PLACARD

89 F1131031624400 1 PLACARD

90 F1131031620600 1 PLACARD

91 F1131031624500 1 PLACARD

93 F3611549200095 1 SUPPORT

94 NAS6603-10 5 BOLT

95 F3611549000000 1 SUPPORT

109 35597-3-255 1 SNSGELEM

110 35587-2-255 1 SNSGELEM

111 35627-2-255 1 SNSGELEM

112 35625-2-255 1 SNSGELEM

References

Fig. A-FBLAA

Installation of the New Sensing

Elements between FR53.6 and FR55 on

LH side

Sheet 01

Sheet 02

Sheet 03

Sheet 04

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 381

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@A340

SERVICE BULLETIN

(a) Install the sensing elements and the supports between FR53.6 and FR55.

1 Install the supports between FR53.6 and FR55 :

1 Support F3611548300000 Item 70

1 Support F3611549100000 Item 79

1 Support F3611549200095 Item 93

1 Support F3611549000000 Item 95

1 Angle NSA5546-00 Item 30

2 Rivet-Blind ASNA0342T04-01 Item 11

27 Clamp NSA5543-00 Item 10

3 Clamp NSA5538-00 Item 86

6 Spacer NSA5527-03-01 Item 16

2 Spacer NSA5527-03-10 Item 17

5 Spacer NSA5527-03-11 Item 18

32 Washer ASNA2397-10L Item 14

17 Bolt NAS6603-1 Item 20

1 Bolt NAS6603-9 Item 21

2 Bolt NAS6603-32 Item 26

2 Bolt NAS6603-2 Item 29

5 Bolt NAS6603-17 Item 87

5 Bolt NAS6603-10 Item 94

2 Install the placards between FR53.6 and FR55 :

1 Placard F1131031620500 Item 88

1 Placard F1131031624400 Item 89

1 Placard F1131031620600 Item 90

1 Placard F1131031624500 Item 91

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 382

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@A340

SERVICE BULLETIN

3 Install the sensing elements between FR53.6 and FR55 :

FIN 24HF

1 Sensing Element 35597-3-255 Item 109

FIN 311HF

1 Sensing Element 35587-2-255 Item 110

FIN 25HF

1 Sensing Element 35627-2-255 Item 111

FIN 312HF

1 Sensing Element 35625-2-255 Item 112

2 Nut NSA5542-00 Item 15

2 Connector NSA5549-90 Item 85

55 Sleeve-Protective NSA5539S Item 13

NOTE: Secure the nuts Item 15 with wire-lock MS20995C32 Item 27.

(19) Subtask 364033-010-004-001 - If necessary, remove the ducts between FR39 and

FR40 for access.

Work Zones and Access Panels

Zone Access/Work location

190

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills AIRFRAME

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-010-801

Fig. A-FBPAA

Removal/Installation of the Ducts

Between FR39 and FR40 for Access

Sheet 01

(a) Remove :

Fig. A-FBPAA

(Refer to AMM Task 21-20-00-010-801)

1 Duct assy Item (125) Retain

1 Duct assy Item (126) Retain

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1 Duct assy Item (127) Retain

(20) Subtask 364033-831-013-001 - Install the new supports for the new harness

between FR39.1 and FR39.2.

Work Zones and Access Panels

Zone Access/Work location

190

Manpower Resources

Manhours 3.00

Minimum number of person 1

Subtask elapsed time 3.00

Skills AIRFRAME

Material necessary to do the job

Kit 364033A01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

63 ASNA2327-3-8 2 SUPPORT

64 F5391094700095 1 PLATE

65 NSA5456-3-8 1 SUPPORT

97 ASNA2050DCJ3215 14 RIVET

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Corrosion Inhibiting Brush

Consistency

09-013B As required

References

Fig. A-FBNAA

Installation of the Supports for the New

Harness

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

(a) At FR39.1, remove a support between STGR 37 and STGR 38.

Fig. A-FBNAA Sheet 02 and Fig. A-FBNAA Sheet 03

1 Remove :

2 Rivet Item (97) Discard

1 Support Item (88) Retain

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2 Install :

2 Rivet ASNA2050DCJ3215 Item 97

NOTE: Wet install the fasteners with :

Corrosion Inhibiting

Brush Consistency

09-013B As required

(b) At FR39.1, install a support between STGR 37 and STGR 38.

Fig. A-FBNAA Sheet 02 and Fig. A-FBNAA Sheet 03

1 Put the support Item (88) in position as shown on Fig. A-FBNAA Sheet 03.

2 Drill two holes on the structure to a diameter comprised between 3.25mm

(0.128in.) and 3.35mm (0.132in.) to match the holes of the support Item (88).

3 Install :

1 Support Item (88) Retained at

removal

2 Rivet ASNA2050DCJ3215 Item 97

NOTE: Wet install the fasteners with :

Corrosion Inhibiting

Brush Consistency

09-013B As required

(c) At FR39.2, install a plate between STGR 46 and STGR 47.

Fig. A-FBNAA Sheet 02 and Fig. A-FBNAA Sheet 04

1 Remove :

2 Rivet Item (97) Discard

1 Support Item (89) Retain

2 Put the plate Item 64 in position as shown on Fig. A-FBNAA Sheet 04.

3 Drill one hole on the plate Item 64 to a diameter comprised between 3.25mm

(0.128in.) and 3.35mm (0.132in.) to match the hole of the structure.

4 Drill three holes on the structure to a diameter comprised between 3.25mm

(0.128in.) and 3.35mm (0.132in.) to match the holes of the plate Item (64).

5 Install :

1 Plate F5391094700095 Item 64

4 Rivet ASNA2050DCJ3215 Item 97

NOTE: Wet install the fasteners with :

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Corrosion Inhibiting

Brush Consistency

09-013B As required

(d) At FR39.2, install two supports between STGR46 and STGR48.

Fig. A-FBNAA Sheet 02 and Fig. A-FBNAA Sheet 04

1 Put the supports Item 63 in position as shown on Fig. A-FBNAA Sheet 04.

2 Drill four holes on the structure to a diameter comprised between 3.25mm

(0.128in.) and 3.35mm (0.132in.) to match the holes of the supports Item 63.

3 Install :

2 Support ASNA2327-3-8 Item 63

4 Rivet ASNA2050DCJ3215 Item 97

NOTE: Wet install the fasteners with :

Corrosion Inhibiting

Brush Consistency

09-013B As required

(e) At FR39.1, install a support between STGR 39 and STGR 40.

Fig. A-FBNAA Sheet 02 and Fig. A-FBNAA Sheet 05

1 Put the support Item 65 in position as shown on Fig. A-FBNAA Sheet 05.

2 Drill two holes on the structure to a diameter comprised between 3.25mm

(0.128in.) and 3.35mm (0.132in.) to match the holes of the support Item 65.

3 Install :

1 Support NSA5456-3-8 Item 65

2 Rivet ASNA2050DCJ3215 Item 97

NOTE: Wet install the fasteners with :

Corrosion Inhibiting

Brush Consistency

09-013B As required

(21) Subtask 364033-831-014-001 - Install the Interconnecting Electrical Wire FIN 309HF

and 310HF, between the sensing elements.

Work Zones and Access Panels

Zone Access/Work location

150

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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Manpower Resources

Manhours 3.00

Minimum number of person 1

Subtask elapsed time 3.00

Skills NON SPECIFIC

Material necessary to do the job

Kit 364033A02R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

14 ASNA2397-10L 1 WASHER

18 NSA5527-03-11 1 SPACER

92 NSA57304-643ADL 1 PLATE

155 NSA5516-04ND 1 CLAMP

168 NAS1801-3-22 1 SCREW

169 NSA935401-03 8 TIE

174 35301-74 1 CABLE

175 35301-75 2 CABLE

182 NSA5050-4 1 NUT

F1131031521900 1 PLACARD

F1131031522000 1 PLACARD

F9000095227895 BUNDLE

F9100095005595 1 PLACARD

References

Fig. A-FBCAA

Drilling of a New Hole in the Structure

between FR53.5 and FR53.6 on the LH

side and Installation of Sensing

Elements

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Fig. A-FCCAA

Installation of the Wiring of the New

Sensing Elements

Sheet 01

Sheet 02

(a) Put in position :

FIN 309HF

1 Cable-Electrical

Interconnecting

35301-74 Item 174

(b) Put in position :

FIN 310HF

1 Cable-Electrical

Interconnecting

35301-75 Item 175

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(c) Install the splice FIN 3593VS (PN E0360RK1816) between the FIN 309HF and the

FIN 310HF, supplied in :

Bundle F9000095227895

(d) Identify the splice FIN 3593VS with the identification sleeves and the identification

label supplied in :

1 Placard F9100095005595

and

Bundle F9000095227895

(e) On the fuselage close to the plugs, identify the FIN 309HF and the FIN 310HF with

:

1 Placard F1131031521900

and

1 Placard F1131031522000

(f) Identify the wire No. 3622-0543 of the FIN 310HF and the wire No. 3622-0544 of

the FIN 309HF with the identification sleeves supplied in :

1 Placard F9100095005595

(g) Modify the splice FIN 3503VS :

1 Before any disconnection, record the wires number associated to the FIN

137HF and the FIN 138HF.

2 Remove the splice FIN 3503VS between the FIN 137HF and the FIN 138HF :

FIN 3503VS

1 Splice Discard

NOTE: Retain the identification sleeves and the identification label of

the 3503VS and of the wires associated to the FIN 137HF and

the FIN 138HF.

3 Remove :

FIN 137HF

1 Cable-Electrical

Interconnecting

35301-74 Item (174) Discard

4 Maintain in position :

FIN 138HF

1 Cable-Electrical

Interconnecting

35301-75 Item (175)

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5 Put in position :

FIN 137HF

1 Cable-Electrical

Interconnecting

35301-75 Item 175

6 Install the new splice FIN 3503VS (PN E0360RK1816) between the FIN

137HF and the FIN 138HF, supplied in :

Bundle F9000095227895

NOTE: Identify the splice FIN 3503VS with the identification sleeves

and the identification label retained at removal.

NOTE: In accordance to the wires connections recorded at removal,

identify the wires associated to the FINs 137HF and 138HF

with the retained identification sleeves.

(h) Between Frame 53.5 and Frame 53.6 and as shown in Fig. A-FBCAA Sheet 01 and

Fig. A-FBCAA Sheet 03, install the FINs 137HF and 138HF and the FINs 309HF

and 310HF (spliced previously) with :

1 Spacer NSA5527-03-11 Item 18

1 Clamp NSA5516-04ND Item (155) Retained at

removal

1 Clamp NSA5516-04ND Item 155

1 Washer ASNA2397-10L Item 14

1 Screw NAS1801-3-22 Item 168

and attach it with :

8 Tie-Cable NSA935401-03 Item 169

NOTE: After connection, secure the FINs 137HF and 138HF and the FINs

309HF and 310HF with Wire-lock MS20995C32 item 27, (Refer to

Fig. A-FBCAA Sheet 05).

(i) Secure the FIN 310HF :

Refer to Fig. A-FBCAA Sheet 04

1 Remove :

1 Nut Discard

2 Install :

1 Plate-Attachment NSA57304-643ADL Item 92

With :

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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1 Nut NSA5050-4 Item 182

3 Secure the new nut and the FIN 310HF with wire-lock MS20995C32 item 27,

(Refer to Fig. A-FBCAA Sheet 05).

(22) Subtask 364033-831-015-001 - Install the new Harness 2SG.

Work Zones and Access Panels

Zone Access/Work location

190

Manpower Resources

Manhours 26.00

Minimum number of person 2

Subtask elapsed time 13.00

Skills NON SPECIFIC

Material necessary to do the job

Kit 364033A02R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

14 ASNA2397-10L 4 WASHER

16 NSA5527-03-01 2 SPACER

18 NSA5527-03-11 1 SPACER

22 NSA5527-03-15 1 SPACER

131 NSA935808-03 24 WASHER

134 NSA935807-16 1 CLAMP

135 NSA935807-20 1 CLAMP

141 NSA5527-03-02 3 SPACER

150 NSA935807-04 30 CLAMP

151 NSA5159-17 19 STUD

152 NSA5527-03-08 19 SPACER

153 NSA935808-01 13 WASHER

154 NSA5050-3 28 NUT

157 NSA5159-10 1 STUD

158 NAS1801-3-9 4 SCREW

159 NAS1801-3-8 2 SCREW

163 NSA5159-27 5 STUD

165 NSA5527-03-05 1 SPACER

166 NAS1801-3-12 4 SCREW

167 NAS1801-3-10 3 SCREW

170 MS21042-3 4 NUT

171 NAS1801-3-17 2 SCREW

172 NAS1149F0332P 2 WASHER

173 NSA5527-03-12 6 SPACER

174 35301-74 1 CABLE

176 NSA5516-21ND 5 CLAMP

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ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

177 NSA5516-22ND 5 CLAMP

178 NSA5516-23ND 5 CLAMP

179 NSA5516-07ND 2 CLAMP

180 NSA5516-08ND 2 CLAMP

181 NSA5516-10ND 2 CLAMP

183 NSA934710E20 3 SPRING

184 NSA934710T11 2 FITTING

E0432A04 20 (M) CONDUIT

F1131031522100 1 PLACARD

F9000095227895 BUNDLE

References

Elec. Std. Practices Manual (ESPM) 20-43-42

Fig. A-FBMAA

Installation of the New Harness 2SG

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

Sheet 09

Sheet 10

Sheet 11

Sheet 12

Sheet 13

Sheet 14

Sheet 15

Sheet 16

Sheet 17

Sheet 18

Sheet 19

Sheet 20

Sheet 21

Sheet 22

Fig. A-FCCAA

Installation of the Wiring of the New

Sensing Elements

Sheet 01

Sheet 02

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(a) Install supports of new routing between 302HF located on the left hand side at

stringer 36 and Frame 40 and the 3520VP located on the right hand side at Frame

39.1 :

1 On the left hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03, Fig. A-FBMAA Sheet 04, Fig. A-FBMAA Sheet 05 and Fig. AFBMAA Sheet 06, along the Frame 39.1 and between Frame 39.1 and Frame

39.2, remove :

a For Section A-A :

7 Screw Item (130) Discard

7 Washer Item (131) Discard

7 Clamp Item (150) Retain

2 On the left hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03, Fig. A-FBMAA Sheet 04, Fig. A-FBMAA Sheet 05 and Fig. AFBMAA Sheet 06, along the Frame 39.1 and between Frame 39.1 and Frame

39.2, install :

a For Section B-B :

7 Stud NSA5159-17 Item 151

7 Clamp Item (150) Retained at

removal

7 Spacer NSA5527-03-08 Item 152

7 Clamp NSA935807-04 Item 150

7 Washer NSA935808-03 Item 131

7 Nut NSA5050-3 Item 154

b For Section C-C :

1 Stud NSA5159-17 Item 151

1 Clamp NSA935807-04 Item 150

1 Spacer NSA5527-03-08 Item 152

1 Clamp NSA935807-04 Item 150

1 Washer NSA935808-03 Item 131

1 Nut NSA5050-3 Item 154

NOTE: Install this hardware on the support Item 65 installed

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previously.

3 On the left hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03, Fig. A-FBMAA Sheet 04, Fig. A-FBMAA Sheet 05 , Fig. A-FBMAA

Sheet 07, Fig. A-FBMAA Sheet 08 and Fig. A-FBMAA Sheet 09, along the

Frame 39.1 and between Stringer 39 and 40, remove :

a For Section F-F :

1 Screw Item (130) Discard

1 Washer Item (131) Discard

1 Clamp Item (150) Retain

b For Section G-G :

1 Screw Item (132) Discard

1 Washer Item (133) Discard

1 Clamp Item (155) Retain

4 On the left hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03, Fig. A-FBMAA Sheet 04, Fig. A-FBMAA Sheet 05 , Fig. A-FBMAA

Sheet 07, Fig. A-FBMAA Sheet 08 and Fig. A-FBMAA Sheet 09, along the

Frame 39.1 and between Stringer 39 and 40, install :

a For Section H-H :

1 Stud NSA5159-17 Item 151

1 Clamp Item (150) Retained at

removal

1 Spacer NSA5527-03-08 Item 152

1 Clamp NSA935807-04 Item 150

1 Washer NSA935808-03 Item 131

1 Nut NSA5050-3 Item 154

b For Section J-J :

1 Stud NSA5159-17 Item 151

1 Clamp Item (155) Retained at

removal

1 Spacer NSA5527-03-08 Item 152

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1 Clamp NSA935807-04 Item 150

1 Washer NSA935808-03 Item 131

1 Nut NSA5050-3 Item 154

5 On the left hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 09, along the Frame 39.1 and between

Stringer 40 and 43, remove for detail F :

2 Screw Item (136) Discard

2 Washer Item (137) Discard

2 Clamp Item (135) Retain

2 Clamp Item (134) Retain

6 On the left hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 09, along the Frame 39.1 and between

Stringer 40 and 43, install for detail G :

2 Stud NSA5159-17 Item 151

2 Clamp Item (134) Retained at

removal

2 Clamp Item (135) Retained at

removal

2 Spacer NSA5527-03-08 Item 152

2 Clamp NSA935807-04 Item 150

2 Washer NSA935808-03 Item 131

2 Nut NSA5050-3 Item 154

7 On the left hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03, Fig. A-FBMAA Sheet 10 and Fig. A-FBMAA Sheet 11, along the

Frame 39.1 and between Stringers 44 and 45, remove :

a For Section K-K :

1 Nut Item (154) Discard

1 Washer Item (153) Discard

1 Clamp Item (138) Retain

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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1 Spacer Item (152) Retain

1 Clamp Item (135) Retain

1 Clamp Item (134) Retain

1 Stud Item (151) Retain

Or

1 Nut Item (154) Discard

1 Washer Item (153) Discard

1 Clamp Item (138) Retain

1 Clamp Item (139) Retain

1 Spacer Item (152) Discard

1 Clamp Item (135) Retain

1 Clamp Item (134) Retain

1 Stud Item (151) Discard

8 On the left hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03, Fig. A-FBMAA Sheet 10 and Fig. A-FBMAA Sheet 11, along the

Frame 39.1 and between Stringers 44 and 45, install :

a For Section M-M :

1 Stud Item (151) Retained at

removal

1 Clamp Item (134) Retained at

removal

1 Clamp Item (135) Retained at

removal

1 Spacer Item (152) Retained at

removal

1 Clamp Item (138) Retained at

removal

1 Clamp NSA935807-04 Item 150

1 Washer NSA935808-03 Item 131

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1 Nut NSA5050-3 Item 154

Or

1 Stud NSA5159-27 Item 163

1 Clamp Item (134) Retained at

removal

1 Clamp Item (135) Retained at

removal

2 Spacer NSA5527-03-12 Item 173

1 Clamp Item (139) Retained at

removal

1 Clamp Item (138) Retained at

removal

1 Clamp NSA935807-04 Item 150

1 Washer NSA935808-03 Item 131

1 Nut NSA5050-3 Item 154

9 On the left hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03, Fig. A-FBMAA Sheet 10 and Fig. A-FBMAA Sheet 12, along the

Frame 39.1 and between Stringers 44 and 45, remove :

a For Section L-L :

1 Screw Item (130) Discard

1 Washer Item (153) Discard

1 Clamp Item (135) Retain

1 Clamp Item (134) Retain

10 On the left hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03, Fig. A-FBMAA Sheet 10 and Fig. A-FBMAA Sheet 12, along the

Frame 39.1 and between Stringers 44 and 45, install :

a For Section N-N :

1 Stud NSA5159-17 Item 151

1 Clamp Item (134) Retained at

removal

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1 Clamp Item (135) Retained at

removal

1 Spacer NSA5527-03-08 Item 152

1 Clamp NSA935807-04 Item 150

1 Washer NSA935808-03 Item 131

1 Nut NSA5050-3 Item 154

11 On the left hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03, Fig. A-FBMAA Sheet 13 and Fig. A-FBMAA Sheet 14, along the

Frame 39.1 and between Stringers 46 and 48, remove :

a For Section P-P :

1 Nut Item (154) Discard

1 Washer Item (153) Discard

1 Clamp Item (139) Retain

1 Spacer Item (152) Retain

1 Clamp Item (135) Retain

1 Clamp Item (134) Retain

1 Stud Item (151) Discard

Or

1 Nut Item (154) Discard

1 Washer Item (153) Discard

1 Clamp Item (138) Retain

1 Clamp Item (139) Retain

1 Spacer Item (152) Discard

1 Clamp Item (135) Retain

1 Clamp Item (134) Retain

1 Stud Item (151) Discard

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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12 On the left hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03, Fig. A-FBMAA Sheet 13 and Fig. A-FBMAA Sheet 14, along the

Frame 39.1 and between Stringers 46 and 48, install :

a For Section R-R :

1 Stud NSA5159-17 Item 151

1 Clamp Item (134) Retained at

removal

1 Clamp Item (135) Retained at

removal

1 Spacer Item (152) Retained at

removal

1 Clamp Item (139) Retained at

removal

1 Clamp NSA935807-04 Item 150

1 Washer NSA935808-03 Item 131

1 Nut NSA5050-3 Item 154

Or

1 Stud NSA5159-27 Item 163

1 Clamp Item (134) Retained at

removal

1 Clamp Item (135) Retained at

removal

2 Spacer NSA5527-03-12 Item 173

1 Clamp Item (139) Retained at

removal

1 Clamp Item (138) Retained at

removal

1 Clamp NSA935807-04 Item 150

1 Washer NSA935808-03 Item 131

1 Nut NSA5050-3 Item 154

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13 On the left hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03, Fig. A-FBMAA Sheet 13 and Fig. A-FBMAA Sheet 15, along the

Frame 39.1 and between Stringers 46 and 48, remove :

a For Section Q-Q :

1 Nut Item (154) Discard

1 Washer Item (153) Discard

1 Clamp Item (135) Retain

1 Spacer Item (152) Retain

1 Clamp Item (134) Retain

1 Clamp Item (139) Retain

1 Stud Item (151) Retain

Or

1 Nut Item (154) Discard

1 Washer Item (153) Discard

1 Clamp Item (138) Retain

1 Clamp Item (135) Retain

1 Spacer Item (152) Discard

1 Clamp Item (134) Retain

1 Clamp Item (139) Retain

1 Stud Item (144) Discard

14 On the left hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03, Fig. A-FBMAA Sheet 13 and Fig. A-FBMAA Sheet 15, along the

Frame 39.1 and between Stringers 46 and 48, install :

a For Section S-S :

1 Stud Item (151) Retained at

removal

1 Clamp NSA935807-04 Item 150

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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1 Clamp Item (134) Retained at

removal

1 Spacer Item (152) Retained at

removal

1 Clamp Item (139) Retained at

removal

1 Clamp Item (135) Retained at

removal

1 Washer NSA935808-01 Item 153

1 Nut NSA5050-3 Item 154

Or

1 Stud NSA5159-27 Item 163

1 Clamp NSA935807-04 Item 150

1 Clamp Item (134) Retained at

removal

2 Spacer NSA5527-03-12 Item 173

1 Clamp Item (139) Retained at

removal

1 Clamp Item (138) Retained at

removal

1 Clamp Item (135) Retained at

removal

1 Washer NSA935808-01 Item 153

1 Nut NSA5050-3 Item 154

15 On the left hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 16, along the Frame 39.1 and between

Stringers 49 and 52, remove for detail K :

2 Screw Item (132) Discard

2 Washer Item (153) Discard

2 Clamp Item (138) Retain

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 400

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SERVICE BULLETIN

16 On the left hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 16, along the Frame 39.1 and between

Stringers 49 and 52, install for detail L :

2 Stud NSA5159-17 Item 151

2 Clamp Item (138) Retained at

removal

2 Spacer NSA5527-03-08 Item 152

2 Clamp NSA935807-04 Item 150

2 Washer NSA935808-03 Item 131

2 Nut NSA5050-3 Item 154

17 On the left hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 17, along the Frame 39.1 and between

Stringers 52 and 54, remove for Section T-T :

1 Nut Item (154) Discard

1 Washer Item (153) Discard

1 Clamp Item (138) Retain

1 Spacer Item (141) Retain

1 Clamp Item (138) Retain

1 Stud Item (140) Retain

18 On the left hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 17, along the Frame 39.1 and between

Stringers 52 and 54, install for Section U-U :

1 Stud Item (140) Retained at

removal

1 Clamp Item (138) Retained at

removal

1 Spacer Item (141) Retained at

removal

1 Clamp Item (138) Retained at

removal

1 Clamp NSA935807-04 Item 150

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 401

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SERVICE BULLETIN

1 Washer NSA935808-03 Item 131

1 Nut NSA5050-3 Item 154

19 On the right hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 18, along the Frame 39.1 and near the

Stringers 54, remove for detail N :

1 Screw Item (142) Discard

1 Washer Item (153) Discard

1 Clamp Item (138) Retain

20 On the right hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 18, along the Frame 39.1 and near the

Stringers 54, install for detail P :

1 Stud NSA5159-17 Item 151

1 Clamp Item (138) Retained at

removal

1 Spacer NSA5527-03-08 Item 152

1 Clamp NSA935807-04 Item 150

1 Washer NSA935808-03 Item 131

1 Nut NSA5050-3 Item 154

21 On the right hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 18, along the Frame 39.1 and between

Stringers 54 and 48, remove for detail Q :

3 Screw Item (142) Discard

3 Washer Item (153) Discard

3 Clamp Item (138) Retain

22 On the right hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 18, along the Frame 39.1 and between

Stringers 54 and 48, install for detail R :

3 Clamp NSA935807-04 Item 150

3 Clamp Item (138) Retained at

removal

3 Washer NSA935808-01 Item 153

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 402

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SERVICE BULLETIN

3 Screw NAS1801-3-9 Item 158

23 On the right hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 18, between the Frame 39.1 and Frame

39.2 and between Stringers 48 and 46, install for detail S :

2 Clamp NSA935807-04 Item 150

2 Washer NSA935808-03 Item 131

2 Screw NAS1801-3-8 Item 159

NOTE: Install this hardware on the support Item 63 installed

previously.

24 On the right hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 19, between the Frame 39.1 and Frame

39.2 and between Stringers 48 and 46, install for Section W-W :

2 Spacer NSA5527-03-02 Item 141

2 Clamp NSA5516-07ND Item 179

or

2 Clamp NSA5516-08ND Item 180

or

2 Clamp NSA5516-10ND Item 181

and

2 Washer NAS1149F0332P Item 172

2 Screw NAS1801-3-17 Item 171

NOTE: Depends on aircraft configuration, use the PN NSA5516-07ND

or NSA5516-08ND or NSA5516-10ND for Item 170.

NOTE: Install this hardware on the support Item 64 installed

previously.

25 On the right hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 19, between the Frame 39.1 and Frame

39.2 and between Stringers 48 and 46, install for Section V-V :

1 Stud NSA5159-27 Item 163

1 Spacer NSA5527-03-01 Item 16

1 Clamp NSA935807-16 Item 134

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 403

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SERVICE BULLETIN

1 Spacer NSA5527-03-08 Item 152

1 Clamp NSA935807-20 Item 135

1 Washer NSA935808-01 Item 153

1 Nut NSA5050-3 Item 154

NOTE: Install this hardware on the support Item 64 installed

previously.

26 On the right hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 20, between the Frame 39.1 and Frame

39.2 and between Stringers 47 and 46, remove for detail T :

1 Screw Item (136) Discard

1 Washer Item (153) Discard

1 Clamp Item (135) Retain

1 Clamp Item (134) Retain

27 On the right hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 20, between the Frame 39.1 and Frame

39.2 and between Stringers 47 and 46, install for detail U :

1 Stud NSA5159-17 Item 151

1 Spacer NSA5527-03-02 Item 141

1 Clamp Item (134) Retained at

removal

1 Spacer NSA5527-03-05 Item 165

1 Clamp Item (135) Retained at

removal

1 Washer NSA935808-01 Item 153

1 Nut NSA5050-3 Item 154

28 On the right hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 20, between the Frame 39.1 and Frame

39.2 and between Stringers 47 and 46, remove for detail Y :

1 Screw Item (143) Discard

1 Washer Item (133) Discard

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 404

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SERVICE BULLETIN

1 Clamp Item (155) Retain

1 Clamp Item (155) Retain

29 On the right hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 20, between the Frame 39.1 and Frame

39.2 and between Stringers 47 and 46, install for detail Z :

1 Stud NSA5159-27 Item 163

1 Clamp Item (155) Retained at

removal

1 Clamp Item (155) Retained at

removal

1 Spacer NSA5527-03-08 Item 152

1 Spacer NSA5527-03-15 Item 22

1 Clamp NSA935807-04 Item 150

1 Washer NSA935808-03 Item 131

1 Nut NSA5050-3 Item 154

30 On the right hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 20, between the Frame 39.1 and Frame

39.2 and between Stringers 46 and 45, remove for detail W :

1 Screw Item (136) Discard

1 Washer Item (153) Discard

1 Clamp Item (135) Retain

1 Clamp Item (134) Discard

31 On the right hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 20, between the Frame 39.1 and Frame

39.2 and between Stringers 46 and 45, install for detail X :

1 Stud NSA5159-10 Item 157

And

1 Clamp NSA5516-21ND Item 176

Or

1 Clamp NSA5516-22ND Item 177

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 405

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SERVICE BULLETIN

Or

1 Clamp NSA5516-23ND Item 178

And

1 Spacer NSA5527-03-01 Item 16

1 Spacer NSA5527-03-08 Item 152

1 Clamp Item (135) Retained at

removal

1 Washer NSA935808-01 Item 153

1 Nut NSA5050-3 Item 154

NOTE: Depends on aircraft configuration, use the PN NSA5516-21ND

or NSA5516-22ND or NSA5516-23ND for Item 166.

32 On the right hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 21, between the Frame 39.1 and Frame

39.2 and between Stringers 44 and 43, remove for detail AA :

1 Screw Item (136) Discard

1 Washer Item (153) Discard

1 Clamp Item (135) Retain

1 Clamp Item (134) Discard

33 On the right hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 21, between the Frame 39.1 and Frame

39.2 and between Stringers 44 and 43, install for detail AB :

1 Stud NSA5159-17 Item 151

And

1 Clamp NSA5516-21ND Item 176

Or

1 Clamp NSA5516-22ND Item 177

Or

1 Clamp NSA5516-23ND Item 178

And

1 Spacer NSA5527-03-11 Item 18

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 406

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SERVICE BULLETIN

1 Clamp Item (135) Retained at

removal

1 Washer NSA935808-01 Item 153

1 Nut NSA5050-3 Item 154

NOTE: Depends on aircraft configuration, use the PN NSA5516-21ND

or NSA5516-22ND or NSA5516-23ND for Item 166.

34 On the right hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 21, between the Frame 39.1 and Frame

39.2 and between Stringers 42 and 38, remove for detail AC :

3 Screw Item (136) Discard

3 Washer Item (153) Discard

3 Clamp Item (135) Retain

3 Clamp Item (134) Discard

35 On the right hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 21, between the Frame 39.1 and Frame

39.2 and between Stringers 42 and 38, install for detail AD :

3 Clamp NSA5516-21ND Item 176

Or

3 Clamp NSA5516-22ND Item 177

Or

3 Clamp NSA5516-23ND Item 178

And

3 Clamp Item (135) Retained at

removal

3 Washer NSA935808-01 Item 153

3 Screw NAS1801-3-10 Item 167

NOTE: Depends on aircraft configuration, use the PN NSA5516-21ND

or NSA5516-22ND or NSA5516-23ND for Item 166.

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 407

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SERVICE BULLETIN

36 On the right hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 21, along the Frame 39.1 and between

Stringers 38 and 37, remove for detail AE :

1 Screw Item (153) Discard

1 Washer Item (142) Discard

1 Clamp Item (135) Retain

37 On the right hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 21, between the Frame 39.1 and Frame

39.2 and between Stringers 38 and 37, install for detail AF :

1 Clamp Item (135) Retained at

removal

1 Washer NSA935808-01 Item 153

1 Screw NAS1801-3-9 Item 158

NOTE: Install this hardware on the support Item (88) installed

previously.

(b) Install the new route 2SG between FIN 302HF located on the left hand side at

stringer 36 and Frame 40 and the FIN 3520VC located in the avionics compartment

:

1 Remove the pressure seal 3520VP :

Refer to ESPM 20-43-42 and to Fig. A-FBMAA Sheet 22

a Remove :

2 Fitting-Seal NSA934710T11 Item (184) Discard

And

3 Spring NSA934710E20 Item (183) Discard

Attached with :

4 Screw NAS1801-3-12 Item (166) Discard

4 Washer ASNA2397-10L Item (14) Discard

4 Nut MS21042-3 Item (170) Discard

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 408

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SERVICE BULLETIN

2 Put in position :

FIN 301HF

1 Cable-Electrical

Interconnecting

35301-74 Item 174

3 Install :

20 (M) Conduit E0432A04

4 Using supports installed at paragraph 3.C.(20).(a), route the wire No.

3622-0540 spliced at paragraph 3.C.(20).(b).2, from FIN 301HF located on the

left hand side at stringer 36 and at Frame 40, through pressure seal 3520VP,

to 3520VC located in avionics compartment as shown in Fig. A-FCCAA Sheet

01 and in Fig. A-FBMAA Sheet 01.

NOTE: The route 2SG rejoins route 2S on the right hand side at

stringer 46 between Frame 39.1 and Frame 39.2 as shown in

Fig. A-FBMAA Sheet 17.

5 Connect the wire No. 3622-0540 as shown on the wiring diagram, Fig. AFCCAA Sheet 01 and as given in the Hook-up Chart lines :

- 1 and 2 (Refer to Fig. A-FCCAA Sheet 02).

NOTE: Use the contacts supplied in :

Bundle F9000095227895

6 Install the splice FIN 3591VS (PN NSA936809RG0002) between the FIN

301HF and the wire No. 3622-0540 supplied in :

Bundle F9000095227895

NOTE: After connection, Secure the FIN 301HF and FIN 302HF with

Wire-lock MS20995C32 item 27.

7 Install the pressure seal 3520VP :

Refer to ESPM 20-43-42 and to Fig. A-FBMAA Sheet 22

a Install :

2 Fitting-Seal NSA934710T11 Item 184

And

3 Spring NSA934710E20 Item 183

Attach with :

4 Screw NAS1801-3-12 Item 166

4 Washer ASNA2397-10L Item 14

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 409

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SERVICE BULLETIN

4 Nut MS21042-3 Item 170

8 Identify the splice FIN 3591VS with the identification sleeves and the

identification label supplied in :

Bundle F9000095227895

9 On the fuselage close to the plugs, identify the FIN 301HF with :

1 Placard F1131031522100

(23) Subtask 364033-831-201-001 - Install the electrical wiring in the FWD cargo

compartment

Work Zones and Access Panels

Zone Access/Work location

130 Work location from Frame 19 to Frame 37.1

Manpower Resources

Manhours 7.50

Minimum number of person 2

Subtask elapsed time 3.50

Skills ELECTRICAL

Material necessary to do the job

Kit 364033D01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

400 F9297000500000 1 EQUIPMNT

402 F9237000207400 2 PLCRDSET

404 NSA935401-03 100 TIE

405 NSA935401-04 100 TIE

406 NSA935401-05 100 TIE

407 NSA935401-10 100 TIE

References

Fig. A-GBAAA

Installation of the Electrical Wiring in the

FWD Cargo Compartment

Sheet 01

Fig. A-GHAAA

Hook-up Chart

Sheet 01

Fig. A-GHBAA

Hook-up Chart

Sheet 01

Fig. A-GWAAA

Wiring Diagram

Sheet 01

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 410

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SERVICE BULLETIN

(a) Install the electrical wiring in the FWD cargo compartment

1 Install the electrical wires:

Refer to Fig. A-GBAAA Sheet 01

Refer to Fig. A-GHAAA Sheet 01, Line 1 thru 2, END 1,

Refer to Fig. A-GWAAA Sheet 01

supplied with:

1 Equipment AssyElectricalF9297000500000 Item 400

2 Attach the electrical wires with:

Refer to Fig. A-GBAAA Sheet 01

100 Tie-Cable NSA935401-03 Item 404

100 Tie-Cable NSA935401-04 Item 405

100 Tie-Cable NSA935401-05 Item 406

100 Tie-Cable NSA935401-10 Item 407

Install the identification placards

2 Placard Set F9237000207400 Item 402

(24) Subtask 364033-831-202-001 - Install the electrical wiring in the AFT cargo

compartment and Bulk cargo compartment

Work Zones and Access Panels

Zone Access/Work location

From 150 Work location Frame 55

To 170 Work location Frame 80

Manpower Resources

Manhours 11.00

Minimum number of person 2

Subtask elapsed time 5.50

Skills ELECTRICAL

Material necessary to do the job

Kit 364033D01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

400 F9297000500000 1 EQUIPMNT

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 411

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SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

402 F9237000207400 4 PLCRDSET

404 NSA935401-03 100 TIE

405 NSA935401-04 100 TIE

406 NSA935401-05 100 TIE

407 NSA935401-10 100 TIE

References

Fig. A-GBBAA

Installation of the Electrical Wiring in the

AFT Cargo Compartment

Sheet 01

Sheet 02

Fig. A-GHAAA

Hook-up Chart

Sheet 01

Fig. A-GHBAA

Hook-up Chart

Sheet 01

Fig. A-GWAAA

Wiring Diagram

Sheet 01

(a) Install the electrical wiring in the AFT cargo compartment and Bulk cargo

compartment

1 Install the electrical wires on 5866VB between Frame 55 thru Frame 80/82:

Refer to Fig. A-GBBAA Sheet 01

Refer to Fig. A-GWAAA Sheet 01

Refer to Fig. A-GHAAA Sheet 01, Line 1 thru 3, END 1,

supplied with:

1 Equipment AssyElectricalF9297000500000 Item 400

2 Attach the electrical wires with:

Refer to Fig. A-GBBAA Sheet 01

100 Tie-Cable NSA935401-03 Item 404

100 Tie-Cable NSA935401-04 Item 405

100 Tie-Cable NSA935401-05 Item 406

100 Tie-Cable NSA935401-10 Item 407

Install the identification placards

4 Placard Set F9237000207400 Item 402

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 412

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@A340

SERVICE BULLETIN

3 Route the electrical wires through the thermal insulator at Frame 80/82:

Refer to Fig. A-GBBAA Sheet 02

1 Insulator-Cable

Protection

ABS0596S006 Item (403)

(25) Subtask 364033-831-203-001 - Modify the electrical wiring in the AFT cargo

compartment, Bulk cargo compartment and Rear fuselage section

Manpower Resources

Manhours 4.50

Minimum number of person 1

Subtask elapsed time 4.50

Skills ELECTRICAL

References

Fig. A-GBCAA

Preparation for the Electrical Wiring

Installation in the Rear Fuselage Section

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

Sheet 09

Sheet 10

Fig. A-GHAAA

Hook-up Chart

Sheet 01

Fig. A-GHBAA

Hook-up Chart

Sheet 01

(a) Remove the pressure seal 5208VP from the pressure Frame at Frame 80/82

Refer to Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet 03

Remove:

1 Plate F9249011000200 Item (410) Retain

1 Plate F9249011000400 Item (411) Retain

2 Bulkhead Item (415) Discard

8 Screw Item (416) Discard

12 Washer Item (417) Discard

4 Washer Item (418) Discard

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 413

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@A340

SERVICE BULLETIN

4 Nut Item (419) Discard

or if alternate installed remove:

12 Washer Item (417) Discard

4 Washer Item (418) Discard

4 Nut Item (419) Discard

4 Screw Item (420) Discard

2 Screw Item (423) Discard

(b) Remove the lightning protection of the electrical bundle 5886VB at Frame 90

Refer to Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet 08

1 At Frame 90 loosen the electrical receptacle 5215VC, Item (435).

Refer to Fig. A-GBCAA Sheet 04 thru Fig. A-GBCAA Sheet 05

4 Screw Item (430) Discard

4 Washer Item (431) Discard

4 Nut Item (432) Discard

2 Disconnect the electrical wires end from the electrical receptacle 5215VC.

Refer to Fig. A-GBCAA Sheet 04 thru Fig. A-GBCAA Sheet 05

Refer to Fig. A-GHAAA Sheet 01 END 2, Line 4 thru 25 Fig. A-GHBAA Sheet

01 END 2, Line 1 and 2

Remove:

1 Receptacle Item (435) Retain

3 Remove from Frame 91

Refer to Fig. A-GBCAA Sheet 04 thru Fig. A-GBCAA Sheet 05

1 Screw Item (314) Discard

1 Washer Item (417) Discard

1 Clamp Item (437) Discard

1 Clip nut Item (353) Discard

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 414

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SERVICE BULLETIN

4 Remove the lightning protection from the electrical bundle 5886VB at Frame

90

Refer to Fig. A-GBCAA Sheet 04 thru Fig. A-GBCAA Sheet 08

8 Screw Item (314) Discard

12 Washer Item (417) Discard

3 Nut Item (419) Discard

21 Clamp Item (437) Retain

3 Spacer Item (442) Retain

1 Clamp Item (443) Retain

4 Screw Item (444) Discard

1 Clip nut Item (448) Discard

or if alternate installed remove:

1 Washer Item (417) Discard

2 Spacer Item (442) Retain

3 Clamp Item (437) Retain

1 Clip nut Item (439) Discard

1 Screw Item (501) Discard

(c) Disconnect the electrical wiring 5865VB from the APU overhead leak detection

system at Frame 93

Refer to Fig. A-GBCAA Sheet 01, Fig. A-GBCAA Sheet 09 thru Fig. A-GBCAA

Sheet 10

Refer to Fig. A-GHAAA Sheet 01

1 Remove between Frame 92 thru Frame 93:

Refer to Fig. A-GBCAA Sheet 09 thru Fig. A-GBCAA Sheet 10

1 Washer Item (417) Discard

1 Nut Item (419) Discard

2 Clamp Item (437) Retain

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 415

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@A340

SERVICE BULLETIN

1 Screw Item (449) Discard

1 Spacer Item (464) Retain

1 Screw Item (465) Discard

1 Nut Item (470) Discard

1 Washer Item (471) Discard

2 Remove from Frame 93:

Refer to Fig. A-GBCAA Sheet 09

2 Washer Item (417) Discard

4 Spacer Item (442) Retain

2 Clamp Item (437) Retain

2 Clip nut Item (448) Discard

2 Screw Item (501) Discard

3 Remove the electrical splice 5151VSA from Frame 93:

Refer to Fig. A-GBCAA Sheet 09 thru Fig. A-GBCAA Sheet 10

Refer to Fig. A-GHAAA Sheet 01 END 2, Line 4 and 5

1 Sleeve Item (479) Discard

1 Sleeve Item (480) Discard

1 Splice Item (481) Discard

(26) Subtask 364033-831-205-001 - Install an additional profile in the Rear fuselage

section

Work Zones and Access Panels

Zone Access/Work location

310 Work location from Frame 90 to Frame 91

Stringer 6RH

Manpower Resources

Manhours 3.00

Minimum number of person 1

Subtask elapsed time 3.00

Skills AIRFRAME

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 416

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SERVICE BULLETIN

Material necessary to do the job

Kit 364033D03R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

314 NAS1801-3-8 2 SCREW

460 F5397083308600 1 SECTION

461 MS21047L3 1 NUT

462 EN6101AD3-08 2 RIVET

463 NAS1149D0332J 2 WASHER

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Corrosion Inhibitive interfay

Sealant

09-005

Corrosion Inhibiting, Fillet

Consistency

09-016 As required

Corrosion Inhibiting low

Adhesion Sealant

09-018

References

Fig. A-GBEAA

Installation of the Bracket between FR90

and FR91

Sheet 01

(a) Install an additional profile in the Rear fuselage section

1 Between Frame 90 thru Frame 91, at RH STGR6, temporarily put into position

Refer to Fig. A-GBEAA Sheet 01

1 Section Assy F5397083308600 Item 460

2 Transfer drill the holes and open holes to final dimension and install:

1 Nut MS21047L3 Item 461

with:

2 Rivet EN6101AD3-08 Item 462

NOTE: For dimensions refer to the table on Fig. A-GBEAA Sheet 01.

3 Between Frame 90 thru Frame 91, at RH STGR6, install:

1 Section Assy F5397083308600 Item 460

with:

2 Screw NAS1801-3-8 Item 314

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 417

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SERVICE BULLETIN

2 Washer NAS1149D0332J Item 463

and protect the surface with:

Corrosion Inhibitive

interfay Sealant

09-005 As required

and

Corrosion Inhibiting,

Fillet Consistency

09-016 As required

, and seal the edges with:

Corrosion Inhibiting

low Adhesion

Sealant

09-018 As required

(27) Subtask 364033-831-204-001 - Install the electrical wiring in the rear fuselage

section

Work Zones and Access Panels

Zone Access/Work location

310 Work location from Frame 80/82 to Frame 93

Manpower Resources

Manhours 14.00

Minimum number of person 2

Subtask elapsed time 7.00

Skills ELECTRICAL

Material necessary to do the job

Kit 364033D01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

314 NAS1801-3-8 8 SCREW

320 NSA5527-03-02 5 SPACER

350 AS21919WCH13 6 CLAMP

351 MS21919WCH14 1 CLAMP

352 MS21919WCH8 1 CLAMP

353 NSA5067-3-1 1 NUT

400 F9297000500000 1 EQUIPMNT

402 F9237000207400 10 PLCRDSET

404 NSA935401-03 100 TIE

405 NSA935401-04 100 TIE

406 NSA935401-05 50 TIE

415 NSA934710T14 2 FITTING

416 NAS1801-3-9 8 SCREW

417 NAS1149C0332R 24 WASHER

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 418

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SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

418 NAS1149D0363K 4 WASHER

419 NAS1291C3M 10 NUT

420 NAS1102-3-10 4 SCREW

423 NAS1801-3-10 2 SCREW

430 NAS1100-04-6 4 SCREW

431 NAS1149CN416R 4 WASHER

432 MS21042-04 4 NUT

439 NSA5066-3-1 1 NUT

444 NAS1801-3-18 3 SCREW

448 NSA5066-3-2 1 NUT

449 NAS1801-08-8 2 SCREW

451 F9249016013200 1 PROTSYS

465 NAS1801-3-15 1 SCREW

469 ASNA0182-4ADL 2 STRIP

470 NAS1291C08M 3 NUT

471 NAS1149CN816R 5 WASHER

472 ASNA0182-3ADL 1 STRIP

475 NAS1801-08-36 2 SCREW

476 NSA5066-08-1 2 NUT

479 E0718-01 0.06 TUBING

480 NSA937210MB0300 0.1 TUBING

481 NSA936809RG0001 2 SPLICE

485 NSA934710E20 3 SPRING

488 E0126-06L 0.2 TUBING

489 F9249016510800 1 PROTSYS

492 ABS0580A17P 1 FITTING

493 NAS1801-3-21 2 SCREW

494 NSA935808C03 2 WASHER

496 NSA5527-03-08D 2 SPACER

501 NAS1801-3-27 2 SCREW

510 E0126-01L 0.35 TUBING

511 F9249016110900 1 PROTSYS

515 AS21919WCH07 1 CLAMP

517 ABS0513-09 1 SUPPORT

518 ABS0520-07P 1 NUT

521 AS21919WCH14 1 CLAMP

528 NAS1801-08-12 1 SCREW

536 AS21919WCH02 3 CLAMP

537 AS21919WCH09 1 CLAMP

843 MS21919WCH12 1 CLAMP

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 419

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SERVICE BULLETIN

References

Fig. A-GBDAA

Installation of the Electrical Wiring in the

Rear Fuselage Section

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

Sheet 09

Sheet 10

Sheet 11

(a) Install the electrical wire in the rear fuselage section

1 Install the electrical wire, Item 400, on 5866VB between Frame 80/82 thru

Frame 90

Refer to Fig. A-GBDAA Sheet 01

1 Equipment AssyElectricalF9297000500000 Item 400

Attach the wire with:

2 Placard Set F9237000207400 Item 402

100 Tie-Cable NSA935401-03 Item 404

100 Tie-Cable NSA935401-04 Item 405

50 Tie-Cable NSA935401-05 Item 406

2 Install the electrical wire on 5866VB with the pressure seal 5208VP at Frame

80/82

Refer to Fig. A-GBDAA Sheet 01 thru Fig. A-GBDAA Sheet 03

Install:

1 Plate F9249011000200 Item (410) Retained at

removal

1 Plate F9249011000400 Item (411) Retained at

removal

with:

2 Fitting-Seal NSA934710T14 Item 415

8 Screw NAS1801-3-9 Item 416

12 Washer NAS1149C0332R Item 417

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 420

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SERVICE BULLETIN

4 Washer NAS1149D0363K Item 418

4 Nut NAS1291C3M Item 419

4 Screw NAS1102-3-10 Item 420

2 Screw NAS1801-3-10 Item 423

NOTE: Alternative to two of the, Item 416.

3 Spring NSA934710E20 Item 485

3 Install the lightning protection of the electrical bundle 5886VB at Frame 90.

Attach to the wires on 5866VB leaving thru the 3 way transition at Frame 90

Refer to Fig. A-GBDAA Sheet 04

0.1 Tubing-Heat-Shrinkable E0126-06L Item 488

NOTE: Cut the sleeve to the necessary length.

4 Route the wires on 5866VB between Frame 90 thru Frame 91

Refer to Fig. A-GBDAA Sheet 04, Fig. A-GBDAA Sheet 08 thru Fig. A-GBDAA

Sheet 09

Install:

1 Protection SystemLightningF9249016510800 Item 489

with:

1 Washer NAS1149C0332R Item 417

1 Screw NAS1801-3-18 Item 444

1 Clamp AS21919WCH13 Item 350

1 Clamp Item (437) Retained at

removal

1 Spacer Item (442) Retained at

removal

5 Route the electrical wires:

Refer to Fig. A-GBDAA Sheet 04 and Fig. A-GBDAA Sheet 08

1 Fitting-Conduit ABS0580A17P Item 492

and install, Item 492, at Frame 90 with:

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 421

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SERVICE BULLETIN

1 Clamp MS21919WCH14 Item 351

2 Nut NAS1291C3M Item 419

1 Strip ASNA0182-4ADL Item 469

2 Screw NAS1801-3-21 Item 493

2 Washer NSA935808C03 Item 494

2 Spacer NSA5527-03-08D Item 496

1 Clamp MS21919WCH12 Item 843

6 Route the electrical wires on 5866VB between Frame 90 thru Frame 91 to

connector 5215VC

Refer to Fig. A-GBDAA Sheet 04 thru Fig. A-GBDAA Sheet 08

Reinstall the connector 5215VC

1 Receptacle Item (435) Retained at

removal

attached with:

4 Screw NAS1100-04-6 Item 430

4 Washer NAS1149CN416R Item 431

4 Nut MS21042-04 Item 432

and install:

1 Screw NAS1801-3-8 Item 314

1 Washer NAS1149C0332R Item 417

2 Clamp Item (437) Retained at

removal

1 Nut-Clip NSA5066-3-2 Item 448

or alternative install:

1 Washer NAS1149C0332R Item 417

3 Clamp Item (437) Retained at

removal

1 Nut-Clip NSA5066-3-1 Item 439

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 422

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2 Spacer Item (442) Retained at

removal

1 Screw NAS1801-3-27 Item 501

and install:

12 Clamp Item (437) Retained at

removal

2 Spacer Item (442) Retained at

removal

5 Clamp AS21919WCH13 Item 350

8 Washer NAS1149C0332R Item 417

7 Screw NAS1801-3-8 Item 314

1 Screw NAS1801-3-27 Item 501

2 Spacer NSA5527-03-02 Item 320

3 Nut NAS1291C3M Item 419

2 Screw NAS1801-3-18 Item 444

1 Nut NSA5067-3-1 Item 353

7 Route the wire, Item 400, from the 3 way transition, Item 492, to the splice

5410VS and route to the wire 5866VB with:

Refer to Fig. A-GBDAA Sheet 04 and Fig. A-GBDAA Sheet 08

1 Protection SystemLightningF9249016013200 Item 451

1 Protection SystemLightningF9249016510800 Item 489

1 Protection SystemLightningF9249016110900 Item 511

0.1 Tubing-Heat-Shrinkable E0126-06L Item 488

0.35 Tubing-Heat-Shrinkable E0126-01L Item 510

NOTE: Cut the sleeve to the necessary length.

and install:

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 423

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SERVICE BULLETIN

8 Placard Set F9237000207400 Item 402

8 Install the protection, Item 511, at Frame 93 with:

1 Nut ABS0520-07P Item 518

1 Support-Strain Relief ABS0513-09 Item 517

9 Install the electrical wire at Frame 93on 5865VB and 5866VB with:

Refer to Fig. A-GBDAA Sheet 01 and Fig. A-GBDAA Sheet 10 thru Fig. AGBDAA Sheet 11

Install:

3 Spacer NSA5527-03-02 Item 320

1 Clamp MS21919WCH8 Item 352

1 Washer NAS1149C0332R Item 417

1 Nut NAS1291C3M Item 419

6 Clamp Item (437) Retained at

removal

5 Spacer Item (442) Retained at

removal

2 Screw NAS1801-08-8 Item 449

1 Screw NAS1801-3-15 Item 465

1 Strip ASNA0182-4ADL Item 469

3 Nut NAS1291C08M Item 470

5 Washer NAS1149CN816R Item 471

1 Strip-Bonding ASNA0182-3ADL Item 472

2 Screw NAS1801-08-36 Item 475

2 Nut-Clip NSA5066-08-1 Item 476

1 Clamp AS21919WCH07 Item 515

1 Clamp AS21919WCH14 Item 521

1 Screw NAS1801-08-12 Item 528

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 424

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SERVICE BULLETIN

3 Clamp AS21919WCH02 Item 536

1 Clamp AS21919WCH09 Item 537

for the wire connection install:

0.06 Tubing-Heat-Shrinkable E0718-01 Item 479

0.1 Tubing-Heat Shrink NSA937210MB0300 Item 480

2 Splice NSA936809RG0001 Item 481

(28) Subtask 364033-831-206-002 - Remove the sensing elements in the AFT and Bulk

cargo compartments

Work Zones and Access Panels

Zone Access/Work location

From 160 Work location Frame 55

To 310 Work location Frame 83

Manpower Resources

Manhours 5.25

Minimum number of person 1

Subtask elapsed time 5.25

Skills ELECTRICAL

References

Fig. A-GBFAB

Removal of the Sensing Elements in the

Bulk and AFT Cargo Compartments

Sheet 01

Sheet 02

Sheet 03

(a) Remove the sensing elements in the AFT and Bulk cargo compartments

1 Remove the sensing elements between Frame 55 thru Frame 83

Refer to Fig. A-GBFAB Sheet 01 thru Fig. A-GBFAB Sheet 03

Remove:

FIN 26HF

1 Sensing Element 35593-2-255 Item (358)

FIN 27HF

1 Sensing Element 35609-2-255 Item (562)

FIN 28HF

1 Sensing Element 35593-2-255 Item (564)

FIN 29HF

1 Sensing Element 35593-2-255 Item (566)

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 425

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FIN 30HF

1 Sensing Element 35609-2-255 Item (563)

FIN 31HF

1 Sensing Element 35609-2-255 Item (570)

FIN 32HF

1 Sensing Element 35609-2-255 Item (572)

attached with:

7 Nut Item (599) Retain

7 Flange Item (592) Discard

17 Sleeve Item (602) Discard

17 Clamp Item (357) Discard

10 Screw Item (620) Retain

10 Spacer Item (609) Discard

16 Clip Nut Item (399) Retain

16 Screw Item (601) Retain

2 Remove the connector of the sensing element at Frame 80/82

Refer to Fig. A-GBFAB Sheet 01 and Fig. A-GBFAB Sheet 03

Remove:

1 Connector Item (355) Discard

2 Washer Item (596) Discard

1 Washer Item (597) Discard

(29) Subtask 364033-831-212-001 - Drill an additional hole for the dual loop overheat

leak detection in the sheet metal pressure bulkhead

Manpower Resources

Manhours 0.75

Minimum number of person 1

Subtask elapsed time 0.75

Skills AIRFRAME

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 426

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SERVICE BULLETIN

References

Fig. A-GBMAA

Hole Location and Dimensions for the

sensing element Installation in the Sheet

Metal Pressure Bulkhead

Sheet 01

(a) Drill the hole for the dual loop overheat leak detection in the pressure bulkhead

For dimensions refer to Fig. A-GBMAA Sheet 01

1 Drill the additional sensing element hole into the pressure bulkhead Frame

80/82 with a diameter of 13.5mm (0.53in.)

(30) Subtask 364033-831-207-002 - Install the sensing elements in the AFT and Bulk

cargo compartments

Work Zones and Access Panels

Zone Access/Work location

From 160 Work location Frame 55

To 310 Work location Frame 83

Manpower Resources

Manhours 11.25

Minimum number of person 1

Subtask elapsed time 11.25

Skills ELECTRICAL

Material necessary to do the job

Kit 364033D11R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

57 D3627006026600 1 PLACARD

355 NSA5549-00 1 CONNECTR

356 F3627011520400 1 PLACARD

357 NSA5543-00 22 CLAMP

358 35587-2-255 2 SNSGELEM

389 F3627011520000 1 PLACARD

562 35602-2-255 2 ELEMENT

563 35600-2-255 2 SNSGELEM

564 35586-2-255 2 ELEMENT

566 35594-2-255 2 SNSGELEM

570 35604-2-255 2 SNSGELEM

572 35597-2-255 1 SNSGELEM

574 35599-3-255 1 ELEMENT

591 F3627011520600 1 PLACARD

592 NSA5546-00 7 ANGLE

593 F3627011522200 1 PLACARD

594 F3627011520800 2 PLACARD

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 427

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SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

596 A2117050220000 1 RING

597 NAS1149C0832R 1 WASHER

602 NSA5539S 176 SLEEVE

604 NAS1149C0863R 1 WASHER

606 F3627011520200 2 PLACARD

607 NAS1919C04S02U 14 RIVET

609 NSA5527-03-01 1 SPACER

610 NSA5538-00 2 CLAMP

611 F3627011521000 1 PLACARD

612 NSA5542-00 6 NUT

805 NAS1802-3-13 1 SCREW

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Lockwire 0.6 Mm 19-018 As required

References

Aircraft Maintenance Manual (AMM) Task 36-22-17-400-801

Fig. A-GBGAB

Installation of the Sensing Elements in

the Bulk and AFT Cargo Compartments

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

Sheet 09

Fig. A-GBNAA

Tolerances for the Waviness and Bend

in the Electrical Wiring

Sheet 01

Sheet 02

(a) Install the sensing elements in the AFT and Bulk cargo compartments

Refer to AMM Task 36-22-17-400-801

1 For the installation of the sensing elements install the connection flanges

Refer to Fig. A-GBGAB Sheet 01 thru Fig. A-GBGAB Sheet 08

Put the angles, Item 592, in position within the given tolerance area, transfer

drill the rivet holes to the duct-brackets with the diameter between 3.28 mm

and 3.35 mm (0.129 in and 0.132 in) and install:

7 Angle NSA5546-00 Item 592

with:

14 Rivet-Blind NAS1919C04S02U Item 607

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 428

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2 Install the sensing elements between Frame 55 thru Frame 83

Refer to Fig. A-GBGAB Sheet 01 thru Fig. A-GBGAB Sheet 08

For the tolerances for waviness and bend in wires, refer to Fig. A-GBNAA

Sheet 01 thru Fig. A-GBNAA Sheet 02.

NOTE: The length compensation of the sensing elements must be

done at the couplings or retainer rings.

NOTE: The sensing elements must be installed in front of the

ventilation holes.

Install:

2 Sensing Element 35587-2-255 Item 358

2 Sensing Element 35602-2-255 Item 562

2 Sensing Element 35600-2-255 Item 563

2 Sensing Element 35586-2-255 Item 564

2 Sensing Element 35594-2-255 Item 566

2 Sensing Element 35604-2-255 Item 570

1 Sensing Element 35597-2-255 Item 572

1 Sensing Element 35599-3-255 Item 574

with:

1 Connector NSA5549-00 Item 355

22 Clamp NSA5543-00 Item 357

16 Clip Nut Item (399) Retained at

removal

6 Screw Item (408) Retained at

removal

1 Ring-Sealing A2117050220000 Item 596

1 Washer NAS1149C0832R Item 597

16 Screw Item (601) Retained at

removal

176 Sleeve-Protective NSA5539S Item 602

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 429

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SERVICE BULLETIN

1 Washer NAS1149C0863R Item 604

1 Spacer NSA5527-03-01 Item 609

2 Clamp NSA5538-00 Item 610

6 Nut NSA5542-00 Item 612

6 Nut Item (599) Retained at

removal

1 Screw NAS1802-3-13 Item 805

NOTE: Secure the nuts, Item 612/(599), with lockwire:

Lockwire 0.6 Mm 19-018 As required

3 Install the identification placards of the sensing-elements between Frame 55

thru Frame 83

Refer to Fig. A-GBGAB Sheet 01 thru Fig. A-GBGAB Sheet 07

Install:

1 Placard F3627011520400 Item 356

1 Placard F3627011520000 Item 389

1 Placard F3627011520600 Item 591

2 Placard F3627011520800 Item 594

1 Placard F3627011522200 Item 593

1 Placard F3627011521000 Item 611

2 Placard F3627011520200 Item 606

1 Placard D3627006026600 Item 57

(31) Subtask 364033-410-003-001 - If removed, install the ducts between FR39 and

FR40.

Work Zones and Access Panels

Zone Access/Work location

190

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 430

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SERVICE BULLETIN

Manpower Resources

Manhours 2.00

Minimum number of person 1

Subtask elapsed time 2.00

Skills AIRFRAME

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801

Fig. A-FBPAA

Removal/Installation of the Ducts

Between FR39 and FR40 for Access

Sheet 01

(a) Install :

Fig. A-FBPAA

(Refer to AMM Task 21-20-00-410-801)

1 Duct assy Item (125) Retained at

removal

1 Duct assy Item (126) Retained at

removal

1 Duct assy Item (127) Retained at

removal

(32) Subtask 364033-831-208-002 - Remove the sensing elements in the rear fuselage

Work Zones and Access Panels

Zone Access/Work location

310 Work location from Frame 80 to Frame 95

Manpower Resources

Manhours 2.75

Minimum number of person 1

Subtask elapsed time 2.75

Skills ELECTRICAL

References

Fig. A-GBHAC

Removal of the Sensing Elements in the

Rear Fuselage Section

Sheet 01

Sheet 02

Sheet 03

Sheet 04

(a) Remove the sensing elements in the rear fuselage

1 Remove the sensing elements between Frame 80/82 thru Frame 95

Refer to Fig. A-GBHAC Sheet 01 thru Fig. A-GBHAC Sheet 04

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 431

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SERVICE BULLETIN

Remove:

FIN 34HF

1 Sensing Element 35301-75 Item (361) Discard

FIN 139HF

1 Sensing Element 35558-2-310 Item (362) Discard

FIN 140HF

1 Sensing Element 35636-2-310 Item (365) Discard

FIN 33HF

1 Sensing Element 35660-2-310 Item (370) Discard

attached with:

3 Screw Item (601) Discard

33 Screw Item (601) Retain

47 Sleeve Item (602) Discard

1 Screw Item (603) Retain

4 Screw Item (620) Retain

5 Spacer Item (609) Retain

40 Clamp Item (357) Discard

37 Nut-Clip Item (399) Retain

3 Flange Item (59) Discard

3 Nut Item (612) Retain

2 Clamp Item (621) Discard

2 Remove the connector of the sensing element at Frame 80/82

Refer to Fig. A-GBHAC Sheet 01 thru Fig. A-GBHAC Sheet 04

Remove:

1 Connector Item (355) Discard

1 Washer Item (596) Discard

1 Washer Item (604) Discard

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 432

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SERVICE BULLETIN

(33) Subtask 364033-831-209-002 - Install the sensing elements in the rear fuselage

Work Zones and Access Panels

Zone Access/Work location

310 Work location from Frame 80 to Frame 95

Manpower Resources

Manhours 5.75

Minimum number of person 1

Subtask elapsed time 5.75

Skills ELECTRICAL

Material necessary to do the job

Kit 364033D14R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

59 NSA5545-00 3 ANGLE

313 NAS1801-3-19 2 SCREW

314 NAS1801-3-8 2 SCREW

355 NSA5549-00 1 CONNECTR

357 NSA5543-00 37 CLAMP

360 35301-74 1 CABLE

361 35301-75 1 CABLE

362 35563-2-255 1 ELEMENT

363 35566-2-255 1 ELEMENT

365 35616-2-255 2 ELEMENT

369 35641-3-255 1 ELEMENT

370 35642-2-255 1 ELEMENT

372 AS21919WCH04 12 CLAMP

373 AS21919WCH10 2 CLAMP

374 F3617052620200 1 PLACARD

392 F3627011521400 1 PLACARD

393 F3627011521600 2 PLACARD

394 F3627011521800 2 PLACARD

397 NSA5527-03-04 2 SPACER

416 NAS1801-3-9 5 SCREW

496 NSA5527-03-08D 1 SPACER

591 F3617052620000 1 PLACARD

596 A2117050220000 1 RING

597 NAS1149C0832R 1 WASHER

602 NSA5539S 94 SLEEVE

604 NAS1149C0863R 1 WASHER

607 NAS1919C04S02U 6 RIVET

608 D3627006026800 1 PLACARD

609 NSA5527-03-01 3 SPACER

610 NSA5538-00 2 CLAMP

612 NSA5542-00 3 NUT

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 433

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@A340

SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

640 MS21042-3 5 NUT

682 NAS1149D0332K 7 WASHER

805 NAS1802-3-13 2 SCREW

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Lockwire 0.6 Mm 19-018 As required

References

Fig. A-GBJAC

Installation of the Sensing Elements in

the Rear Fuselage Section

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

(a) Install the sensing elements in the rear fuselage

1 For the installation of the sensing elements install the connection flanges

Refer to Fig. A-GBJAC Sheet 01 thru Fig. A-GBJAC Sheet 08

Install:

3 Connection Flanges NSA5545-00 Item 59

with:

6 Rivet-Blind NAS1919C04S02U Item 607

2 Install the sensing elements between Frame 80/82 thru Frame 95

Refer to Fig. A-GBJAC Sheet 01 thru Fig. A-GBJAC Sheet 08

NOTE: The length compensation of the sensing elements must be

done at the couplings or retainer rings.

NOTE: The sensing elements must be installed in front of the

ventilation holes.

Install:

FIN 361HF

1 Cable-Electrical

Interconnecting

35301-74 Item 360

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 434

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SERVICE BULLETIN

FIN 34HF

1 Cable-Electrical

Interconnecting

35301-75 Item 361

FIN 139HF

1 Sensing Element 35563-2-255 Item 362

FIN 359HF

1 Sensing Element 35566-2-255 Item 363

FIN 360HF

1 Sensing Element 35616-2-255 Item 365

FIN 140HF

1 Sensing Element 35616-2-255 Item 365

FIN 358HF

1 Sensing Element 35641-3-255 Item 369

FIN 33HF

1 Sensing Element 35642-2-255 Item 370

with:

1 Connector NSA5549-00 Item 355

1 Washer NAS1149C0832R Item 597

1 Ring-Sealing A2117050220000 Item 596

1 Washer NAS1149C0863R Item 604

attached with:

37 Nut-Clip Item (399) Retained at

removal

33 Screw Item (601) Retained at

removal

1 Screw Item (603) Retained at

removal

5 Spacer Item (609) Retained at

removal

3 Nut Item (612) Retained at

removal

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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4 Screw Item (620) Retained at

removal

2 Clamp Item (621) Retained at

removal

2 Screw NAS1801-3-19 Item 313

2 Screw NAS1801-3-8 Item 314

37 Clamp NSA5543-00 Item 357

12 Clamp AS21919WCH04 Item 372

2 Clamp AS21919WCH10 Item 373

2 Spacer NSA5527-03-04 Item 397

5 Screw NAS1801-3-9 Item 416

1 Spacer NSA5527-03-08D Item 496

94 Sleeve-Protective NSA5539S Item 602

3 Spacer NSA5527-03-01 Item 609

2 Clamp NSA5538-00 Item 610

3 Nut NSA5542-00 Item 612

5 Nut MS21042-3 Item 640

7 Washer NAS1149D0332K Item 682

2 Screw NAS1802-3-13 Item 805

NOTE: Secure the nuts, Item 612/(612), with lockwire:

Lockwire 0.6 Mm 19-018 As required

3 Install the identification placards of the sensing-elements between Frame

80/82 thru Frame 95

Refer to Fig. A-GBJAC Sheet 01 thru Fig. A-GBJAC Sheet 08

Install:

1 Placard F3617052620200 Item 374

1 Placard F3627011521400 Item 392

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2 Placard F3627011521600 Item 393

2 Placard F3627011521800 Item 394

1 Placard F3617052620000 Item 591

1 Placard D3627006026800 Item 608

(34) Subtask 364033-831-210-002 - Install the sleeves at the APU Bleed Air Duct

Work Zones and Access Panels

Zone Access/Work location

310 Work location from Frame 80 to Frame 95

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills ELECTRICAL

Material necessary to do the job

Kit 364033D17R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

377 F3617062400400 1 SLEEVE

380 F3617062401600 1 SLEEVE

382 F3617062402200 1 SLEEVE

383 F3617062403200 1 SLEEVE

384 F3617062403400 1 SLEEVE

385 F3617062403600 1 SLEEVE

386 F3617062403800 1 SLEEVE

387 F3617062404000 1 SLEEVE

602 NSA5539S 6 SLEEVE

References

Fig. A-GBKAC

Installation of the Sleeves at the APU

Bleed Air Duct

Sheet 01

(a) Install the sleeves at the APU Bleed Air Duct between Frame 80/82 thru Frame 95

Refer to Fig. A-GBKAC Sheet 01

install the sleeves and close them with the adhesive strips:

1 Sleeve Assy F3617062400400 Item 377

1 Sleeve Assy F3617062401600 Item 380

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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1 Sleeve Assy F3617062402200 Item 382

1 Sleeve F3617062403200 Item 383

1 Sleeve F3617062403400 Item 384

1 Sleeve F3617062403600 Item 385

1 Sleeve F3617062403800 Item 386

1 Sleeve F3617062404000 Item 387

Close the sleeves with:

6 Sleeve-Protective NSA5539S Item 602

NOTE: Make sure that the blowout apertures of the blankets are close to

(under) the sensing elements.

**CONF 005

(1) Subtask 364033-831-016-001 - Modify the Wiring between the Avionics

Compartment and the Cargo Compartment.

Work Zones and Access Panels

Zone Access/Work location

190

Manpower Resources

Manhours 2.00

Minimum number of person 2

Subtask elapsed time 2.00

Skills ELECTRICAL

Material necessary to do the job

Kit 364033A02R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

169 NSA935401-03 300 TIE

F9000095227895 BUNDLE

NSA935401-08 300 TIE

NSA935401-13 300 TIE

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References

Fig. A-FBMAA

Installation of the New Harness 2SG

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

Sheet 09

Sheet 10

Sheet 11

Sheet 12

Sheet 13

Sheet 14

Sheet 15

Sheet 16

Sheet 17

Sheet 18

Sheet 19

Sheet 20

Sheet 21

Sheet 22

Fig. A-FCBAA

Modification of the Wiring between the

Cargo Compartment and the Avionics

Compartment

Sheet 01

Sheet 02

(a) As shown in Fig. A-FBMAA Sheet 01, install the wire, using spares conduits

between Frame 37 and Frame 53.2, as shown on the wiring diagram, Fig. AFCBAA Sheet 01 and as given in the Hook-up Chart line :

- 1 (Refer to Fig. A-FCBAA Sheet 02) supplied in :

Bundle F9000095227895

NOTE: The spares conduits is divided in two parts. The first parts go away

from Frame 40 to Frame 47 and the second parts go away from

Frame 48 to Frame 53.2

(b) Attach the wires with :

300 Tie-Cable NSA935401-03 Item 169

300 Tie-Cable NSA935401-08

300 Tie-Cable NSA935401-13

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(2) Subtask 364033-831-017-001 - Modify the Wiring in the Main rack 800VU.

Work Zones and Access Panels

Zone Access/Work location

120 Work location Electrical panel 800VU

Manpower Resources

Manhours 4.00

Minimum number of person 2

Subtask elapsed time 2.00

Skills ELECTRICAL

Material necessary to do the job

Kit 364033A02R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

169 NSA935401-03 50 TIE

F9000095227895 BUNDLE

NSA935401-06 50 TIE

NSA935401-13 50 TIE

References

Aircraft Maintenance Manual (AMM) Task 36-11-34-000-802

Task 36-11-34-400-802

Fig. A-FCAAA

Modification of the Wiring in the Main

Rack 800VU

Sheet 01

Sheet 02

Sheet 03

Sheet 04

(a) Remove and retain the BMC (FIN 1HA1, 1HA2, 1HA3 and 1HA4) (Refer to AMM

Task 36-11-34-000-802).

(b) Remove the wires as shown on the wiring diagram Fig. A-FCAAA Sheet 01, and as

given in the Hook-up Chart lines :

- 1 thru 5 (Refer to Fig. A-FCAAA Sheet 04).

(c) Install the wires as shown on the wiring diagrams, Fig. A-FCAAA Sheet 02 and Fig.

A-FCAAA Sheet 03 and as given in the Hook-up Chart lines :

- 9 thru 19 (Refer to Fig. A-FCAAA Sheet 04) supplied in :

Bundle F9000095227895

(d) Attach the wires with :

50 Tie-Cable NSA935401-03 Item 169

50 Tie-Cable NSA935401-06

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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50 Tie-Cable NSA935401-13

(e) Install the BMC (FIN 1HA1, 1HA2, 1HA3 and 1HA4) (Refer to AMM Task

36-11-34-400-802).

(3) Subtask 364033-831-001-001 - Remove the sensing elements and the supports

between FR39 and FR44.

Work Zones and Access Panels

Zone Access/Work location

190 Work location from Frame 39 to Frame 44

Manpower Resources

Manhours 4.00

Minimum number of person 1

Subtask elapsed time 4.00

Skills AIRFRAME

References

Aircraft Maintenance Manual (AMM) Task 36-22-17-000-801

Task 36-22-17-000-802

Fig. A-FBAAA

Removal of the Sensing Elements

between FR39 and FR55 on the LH side

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

(a) Remove :

Fig. A-FBAAA Sheet 01 Fig. A-FBAAA Sheet 02

(Refer to AMM Task 36-22-17-000-801 and AMM Task 36-22-17-000-802)

22 Screw Item (20) Discard

32 Washer Item (14) Discard

32 Clamp Item (86) Discard

32 Sleeve Item (13) Discard

5 Screw Item (91) Discard

10 Spacer Item (16) Discard

5 Screw Item (21) Discard

2 Nut Item (15) Discard

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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SERVICE BULLETIN

FIN 97HF

1 Sensing Element 35610-2-255 Item (1) Discard

FIN 98HF

1 Sensing Element 35624-2-255 Item (2) Discard

4 Rivet Item (11) Discard

2 Support Item (10) Discard

(4) Subtask 364033-831-002-001 - Remove the sensing elements and the supports

between FR44 and FR51.

Work Zones and Access Panels

Zone Access/Work location

190 Work location from Frame 44 to Frame 51

Manpower Resources

Manhours 4.00

Minimum number of person 1

Subtask elapsed time 4.00

Skills AIRFRAME

References

Aircraft Maintenance Manual (AMM) Task 36-22-17-000-801

Fig. A-FBAAA

Removal of the Sensing Elements

between FR39 and FR55 on the LH side

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

(a) Remove :

Fig. A-FBAAA Sheet 01 Fig. A-FBAAA Sheet 03

(Refer to AMM Task 36-22-17-000-801)

18 Screw Item (21) Discard

30 Washer Item (14) Discard

30 Clamp Item (86) Discard

30 Sleeve Item (13) Discard

18 Spacer Item (16) Discard

12 Screw Item (20) Discard

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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2 Nut Item (15) Discard

FIN 99HF

1 Sensing Element 35612-2-255 Item (3) Discard

FIN 100HF

1 Sensing Element 35605-2-255 Item (6) Discard

4 Rivet Item (11) Discard

2 Support Item (10) Discard

(5) Subtask 364033-831-003-001 - Remove the sensing elements and the supports

between FR51 and FR53.6.

Work Zones and Access Panels

Zone Access/Work location

190 Work location from Frame 51 to Frame 53.6

Manpower Resources

Manhours 4.00

Minimum number of person 1

Subtask elapsed time 4.00

Skills AIRFRAME

References

Aircraft Maintenance Manual (AMM) Task 36-22-17-000-801

Task 36-22-17-000-802

Fig. A-FBAAA

Removal of the Sensing Elements

between FR39 and FR55 on the LH side

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

(a) Remove :

Fig. A-FBAAA Sheet 01 Fig. A-FBAAA Sheet 04

(Refer to AMM Task 36-22-17-000-801 and AMM Task 36-22-17-000-802)

18 Screw Item (21) Discard

37 Washer Item (14) Discard

37 Clamp Item (86) Discard

37 Sleeve Item (13) Discard

23 Spacer Item (16) Discard

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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16 Screw Item (20) Discard

1 Screw Item (93) Discard

1 Spacer Item (18) Discard

2 Screw Item (91) Discard

3 Nut Item (15) Discard

FIN 101HF

1 Sensing Element 35603-2-255 Item (4) Discard

FIN 102HF

1 Sensing Element 35600-2-255 Item (5) Discard

FIN 23HF

1 Sensing Element 35571-2-255 Item (7) Discard

6 Rivet Item (11) Discard

3 Support Item (10) Discard

(6) Subtask 364033-831-004-001 - Remove the sensing elements and the supports

between FR53.6 and FR55.

Work Zones and Access Panels

Zone Access/Work location

190 Work location from Frame 53.6 to Frame 55

Manpower Resources

Manhours 4.00

Minimum number of person 1

Subtask elapsed time 4.00

Skills AIRFRAME

References

Aircraft Maintenance Manual (AMM) Task 36-22-17-000-801

Fig. A-FBAAA

Removal of the Sensing Elements

between FR39 and FR55 on the LH side

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

(a) Remove :

Fig. A-FBAAA Sheet 01 Fig. A-FBAAA Sheet 05

(Refer to AMM Task 36-22-17-000-801)

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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19 Screw Item (20) Discard

27 Washer Item (14) Discard

27 Clamp Item (86) Discard

27 Sleeve Item (13) Discard

4 Screw Item (91) Discard

12 Spacer Item (16) Discard

4 Screw Item (21) Discard

2 Nut Item (15) Discard

FIN 24HF

1 Sensing Element 35580-2-255 Item (8) Discard

FIN 25HF

1 Sensing Element 35611-3-255 Item (9) Discard

2 Rivet Item (11) Discard

1 Support Item (10) Discard

(7) Subtask 364033-010-002-001 - If necessary, remove the ducts between FR53.5 and

FR53.6 for access.

Work Zones and Access Panels

Zone Access/Work location

150 Work location from Frame 53.5 to Frame 53.6

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills AIRFRAME

References

Aircraft Maintenance Manual (AMM) Task 36-12-41-000-801

Fig. A-FBBAA

Removal/Installation of the Ducts

between FR53.6 and FR53.7 on the LH

side (for Access)

Sheet 01

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(a) Remove :

Fig. A-FBBAA

(Refer to AMM Task 36-12-41-000-801)

1 Duct assy Item (112) Retain

1 Duct assy Item (112) Retain

1 Duct assy Item (114) Retain

(8) Subtask 364033-831-005-001 - Drill a new hole in the structure between FR53.5 and

FR53.6.

Work Zones and Access Panels

Zone Access/Work location

150 Work location from Frame 53.5 to Frame 53.6

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills AIRFRAME

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Chemical Conversion

Coating Yellow Aluminum

13-002 As required

Anti-Corrosion Primer

(polyurethane)

16-001 As required

Polyurethane Finnish Paint 16-018 As required

References

Fig. A-FBCAA

Drilling of a New Hole in the Structure

between FR53.5 and FR53.6 on the LH

side and Installation of Sensing

Elements

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

(a) Drill one hole on the structure between FR53.5 and FR53.6 to a diameter

comprised between 13.5mm (0.531in.) Min. and 13.7mm (0.539 in.) Max. as shown

on Fig. A-FBCAA.

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(b) Do a spotfacing on the structure between FR53.5 and 53.6 to a diameter of 24mm

(0.944 in.) with a radius of 2mm (0.078in.)

NOTE: Be careful at the depth : 2mm (0.078 in.) Min. and 3mm (0.118 in.)

Max.

(c) Protect the hole and the spotfacing with :

Chemical

Conversion Coating

Yellow Aluminum

13-002 As required

Anti-Corrosion

Primer

(polyurethane)

16-001 As required

Polyurethane

Finnish Paint

16-018 As required

(9) Subtask 364033-831-006-001 - Install a new support for the routing of the sensing

elements between FR53.5 and FR53.6.

Work Zones and Access Panels

Zone Access/Work location

150 Work location from Frame 53.5 to Frame 53.6

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills NON SPECIFIC

Material necessary to do the job

Kit 364033A01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

96 F5392059300000 1 SUPPORT

97 ASNA2050DCJ3215 2 RIVET

Reidentified part set REIDA01

ITEM NEW PART N ̊ KEYWORD ITEM OLD PART N ̊ SEE

NOTES

F0041196200000 BLANKET F2581571700000

F2582261900000

F0041196300000 BLANKET F2581566600000

F0041196400000 BLANKET F2581666600000

F0041196500000 BLANKET F2581677800000

F0041196600000 BLANKET F2581677900000

F0041196700000 BLANKET F2582242300000

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Adhesive Tape (insulation

Blanket Repair)

08-073 As required

Interfay Sealant 09-005A As required

Corrosion Inhibiting Fillet

Consistency

09-016B As required

References

Fig. A-FBFAA

Installation of a New Bracket between

FR53.5 and FR53.6

Sheet 01

Sheet 02

(a) Move the insulation blanket to get access to the modification area.

(b) Put the bracket Item 96 in position as shown on Fig. A-FBFAA.

(c) Drill two holes on the structure to a diameter comprised between 3.25mm (0.128in.)

and 3.35mm (0.132in.) to match the holes of the bracket Item 96.

Fig. A-FBFAA

(d) Cut the insulation blanket to permit the installation of the bracket Item 96.

NOTE: For the repair of the insulation blanket use :

Adhesive Tape

(insulation Blanket

Repair)

08-073 As required

(e) Re-identify the insulation blanket :

1 Blanket-Insulation F2581571700000

or

1 Blanket-Insulation F2582261900000

becomes

1 Blanket-Insulation F0041196200000

or

1 Blanket-Insulation F2581566600000

becomes

1 Blanket-Insulation F0041196300000

or

1 Blanket-Insulation F2581666600000

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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becomes

1 Blanket-Insulation F0041196400000

or

1 Blanket-Insulation F2581677800000

becomes

1 Blanket-Insulation F0041196500000

or

1 Blanket-Insulation F2581677900000

becomes

1 Blanket-Insulation F0041196600000

or

1 Blanket-Insulation F2582242300000

becomes

1 Blanket-Insulation F0041196700000

(f) Install :

Fig. A-FBFAA

1 Support F5392059300000 Item 96

2 Rivet ASNA2050DCJ3215 Item 97

NOTE: To the interface of the new bracket and the structure, apply :

Interfay Sealant 09-005A As required

NOTE: Do a sealant bead around new parts with :

Corrosion Inhibiting

Fillet Consistency

09-016B As required

NOTE: Wet install the fasteners with :

Interfay Sealant 09-005A As required

(g) Install the insulation blanket.

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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(10) Subtask 364033-410-001-001 - If removed, install the ducts between FR53.5 and

FR53.6.

Work Zones and Access Panels

Zone Access/Work location

150 Work location from Frame 53.5 to Frame 53.6

Manpower Resources

Manhours 2.00

Minimum number of person 1

Subtask elapsed time 2.00

Skills AIRFRAME

References

Aircraft Maintenance Manual (AMM) Task 36-12-41-400-801

Fig. A-FBBAA

Removal/Installation of the Ducts

between FR53.6 and FR53.7 on the LH

side (for Access)

Sheet 01

(a) Install :

(Refer to AMM Task 36-12-41-400-801)

1 Duct assy Item (112) Retained at

removal

1 Duct assy Item (112) Retained at

removal

1 Duct assy Item (114) Retained at

removal

(11) Subtask 364033-010-003-001 - If necessary, remove the ducts between FR43 and

FR45 for access.

Work Zones and Access Panels

Zone Access/Work location

190 Work location from Frame 43 to Frame 45

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 36-12-41-000-801

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 450

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References

Fig. A-FBDAA

Removal/Installation of the Ducts

between FR44 and FR47 on the LH side

(for Access)

Sheet 01

(a) Remove :

(Refer to AMM Task 36-12-41-000-801)

1 Duct assy Item (115) Retain

1 Duct assy Item (116) Retain

(12) Subtask 364033-831-007-001 - Replace the web assy and the half clamp assy at

FR44.

Work Zones and Access Panels

Zone Access/Work location

190 Work location Frame 44

Manpower Resources

Manhours 3.00

Minimum number of person 1

Subtask elapsed time 3.00

Skills AIRFRAME

Material necessary to do the job

Kit 364033A01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

117 F5331591000200 1 WEB

118 F5331583500200 1 CLAMP

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Corrosion Inhibiting Fillet

Consistency

09-016B As required

Low Adhesion Polysulfide

Sealant

09-019B As required

References

Fig. A-FBEAA

Replacement of the Web Assy at FR44

on the LH side

Sheet 01

Sheet 02

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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(a) Remove :

Fig. A-FBEAA

17 Screw Item (119) Retain

17 Washer Item (124) Retain

1 Strip cover assy Item (122) Retain

2 Screw Item (120) Retain

1 Half clamp assy F5331583500000 Item (118) Discard

1 Half clamp assy Item (121) Retain

1 Bracket Item (123) Retain

1 Web Assy F5331591000000 Item (117) Discard

NOTE: It is not necessary to remove completely the bracket Item (123).

(b) Install :

Fig. A-FBEAA

1 Web Assy F5331591000200 Item 117

1 Bracket Item (123) Retained at

removal

1 Half clamp assy Item (121) Retained at

removal

1 Half clamp assy F5331583500200 Item 118

2 Screw Item (120) Retained at

removal

1 Strip cover assy Item (122) Retained at

removal

17 Washer Item (124) Retained at

removal

17 Screw Item (119) Retained at

removal

NOTE: Install the new web assy with :

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Corrosion Inhibiting

Fillet Consistency

09-016B As required

and

Low Adhesion

Polysulfide Sealant

09-019B As required

(13) Subtask 364033-831-008-001 - Install the new brackets for the routing of the

sensing elements at FR44.

Work Zones and Access Panels

Zone Access/Work location

190 Work location Frame 44

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills AIRFRAME

Material necessary to do the job

Kit 364033A01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

97 ASNA2050DCJ3215 2 RIVET

98 F0041178800000 1 SUPPORT

99 F0041178800100 1 SUPPORT

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Interfay Sealant 09-005A As required

Corrosion Inhibiting Fillet

Consistency

09-016B As required

References

Fig. A-FBGAA

Installation of Two New Brackets at

FR44

Sheet 01

Sheet 02

(a) Put the brackets Item 98 and 99 in position as shown on Fig. A-FBGAA.

(b) Drill two holes to a diameter comprised between 3.25mm (0.128in.) and 3.35mm

(0.132in.) as shown on Fig. A-FBGAA.

(c) Install :

1 Support F0041178800000 Item 98

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 453

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SERVICE BULLETIN

1 Support F0041178800100 Item 99

2 Rivet ASNA2050DCJ3215 Item 97

NOTE: To the interface of the new bracket and the structure apply :

Interfay Sealant 09-005A As required

NOTE: Do a sealant bead around new parts with :

Corrosion Inhibiting

Fillet Consistency

09-016B As required

NOTE: Wet install the fasteners with :

Interfay Sealant 09-005A As required

(14) Subtask 364033-410-002-001 - If removed, install the ducts between FR43 and

FR45.

Work Zones and Access Panels

Zone Access/Work location

190 Work location from Frame 43 to Frame 45

Manpower Resources

Manhours 2.00

Minimum number of person 1

Subtask elapsed time 2.00

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 36-12-41-400-801

Fig. A-FBDAA

Removal/Installation of the Ducts

between FR44 and FR47 on the LH side

(for Access)

Sheet 01

(a) Install :

(Refer to AMM Task 36-12-41-400-801)

1 Duct assy Item (115) Retained at

removal

1 Duct assy Item (116) Retained at

removal

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 454

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@A340

SERVICE BULLETIN

(15) Subtask 364033-831-009-001 - Install the sensing elements and the supports

between FR39 and FR44.

Work Zones and Access Panels

Zone Access/Work location

190 Work location from Frame 39 to Frame 44

Manpower Resources

Manhours 14.00

Minimum number of person 1

Subtask elapsed time 14.00

Skills AIRFRAME

Material necessary to do the job

Kit 364033A01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

10 NSA5543-00 30 CLAMP

11 ASNA0342T04-01 4 BOLT

13 NSA5539S 62 SLEEVE

14 ASNA2397-10L 34 WASHER

15 NSA5542-00 4 NUT

16 NSA5527-03-01 8 SPACER

18 NSA5527-03-11 6 SPACER

20 NAS6603-1 19 BOLT

21 NAS6603-9 8 BOLT

24 NAS6603-15 6 BOLT

29 NAS6603-2 2 BOLT

30 NSA5546-00 2 ANGLE

32 F1131031621700 2 PLACARD

33 F1131031623700 2 PLACARD

34 F1131031621800 1 PLACARD

35 F1131031623800 1 PLACARD

70 F3611548300000 1 SUPPORT

71 F3611548800000 1 SUPPORT

78 F3611549700000 1 SUPPORT

79 F3611549100000 1 SUPPORT

100 35606-2-255 1 SNSGELEM

101 35621-2-255 1 SNSGELEM

102 35620-2-255 1 SNSGELEM

113 35610-2-255 1 SNSGELEM

References

Fig. A-FBHAA

Installation of the New Sensing

Elements between FR39 and FR44 on

LH side

Sheet 01

Sheet 02

Sheet 03

Sheet 04

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 455

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SERVICE BULLETIN

(a) Install the sensing elements and the supports between FR39 and FR40.2.

1 Install the supports between FR39 and FR40 :

1 Angle NSA5546-00 Item 30

2 Rivet-Blind ASNA0342T04-01 Item 11

8 Clamp NSA5543-00 Item 10

6 Spacer NSA5527-03-01 Item 16

2 Spacer NSA5527-03-11 Item 18

8 Washer ASNA2397-10L Item 14

6 Bolt NAS6603-9 Item 21

2 Bolt NAS6603-15 Item 24

2 Install the supports between FR40 and FR40.2 :

1 Support F3611549100000 Item 79

1 Support F3611549700000 Item 78

5 Clamp NSA5543-00 Item 10

1 Spacer NSA5527-03-01 Item 16

8 Washer ASNA2397-10L Item 14

1 Bolt NAS6603-9 Item 21

6 Bolt NAS6603-1 Item 20

2 Bolt NAS6603-2 Item 29

1 Angle NSA5546-00 Item 30

2 Rivet-Blind ASNA0342T04-01 Item 11

3 Install the placards between FR39 and FR40.2 :

2 Placard F1131031621700 Item 32

2 Placard F1131031623700 Item 33

1 Placard F1131031621800 Item 34

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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SERVICE BULLETIN

1 Placard F1131031623800 Item 35

4 Install the sensing elements between FR39 and FR40.2 :

FIN 97HF

1 Sensing Element 35606-2-255 Item 100

FIN 302HF

1 Sensing Element 35610-2-255 Item 113

28 Sleeve-Protective NSA5539S Item 13

4 Nut NSA5542-00 Item 15

NOTE: Secure the nuts Item 15 with wire-lock MS20995C32 Item 27.

(b) Install the sensing elements and the supports between FR40.2 and FR44.

1 Install the supports between FR40.2 and FR44 :

1 Support F3611548300000 Item 70

1 Support F3611548800000 Item 71

17 Clamp NSA5543-00 Item 10

4 Spacer NSA5527-03-11 Item 18

1 Spacer NSA5527-03-01 Item 16

18 Washer ASNA2397-10L Item 14

13 Bolt NAS6603-1 Item 20

1 Bolt NAS6603-9 Item 21

4 Bolt NAS6603-15 Item 24

2 Install the sensing elements between FR40.2 and FR44 :

FIN 98HF

1 Sensing Element 35620-2-255 Item 102

FIN 303HF

1 Sensing Element 35621-2-255 Item 101

34 Sleeve-Protective NSA5539S Item 13

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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SERVICE BULLETIN

(16) Subtask 364033-831-010-001 - Install the sensing elements and the supports

between FR44 and FR50.

Work Zones and Access Panels

Zone Access/Work location

190 Work location from Frame 44 to Frame 50

Manpower Resources

Manhours 14.00

Minimum number of person 1

Subtask elapsed time 14.00

Skills AIRFRAME

Material necessary to do the job

Kit 364033A01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

10 NSA5543-00 29 CLAMP

11 ASNA0342T04-01 4 BOLT

13 NSA5539S 58 SLEEVE

14 ASNA2397-10L 35 WASHER

15 NSA5542-00 8 NUT

16 NSA5527-03-01 11 SPACER

17 NSA5527-03-10 1 SPACER

18 NSA5527-03-11 3 SPACER

19 NAS6603-24 2 BOLT

20 NAS6603-1 14 BOLT

21 NAS6603-9 9 BOLT

23 NAS6603-16 1 BOLT

26 NAS6603-32 1 BOLT

29 NAS6603-2 8 BOLT

30 NSA5546-00 2 ANGLE

34 F1131031621800 1 PLACARD

35 F1131031623800 1 PLACARD

36 F1131031623900 2 PLACARD

37 F1131031621900 2 PLACARD

38 F1131031624000 2 PLACARD

39 F1131031622000 2 PLACARD

40 F1131031622100 1 PLACARD

41 F1131031624100 1 PLACARD

79 F3611549100000 4 SUPPORT

80 F3611549500000 1 SUPPORT

81 F3611549600000 1 SUPPORT

103 35618-2-255 2 SNSGELEM

105 35598-2-255 1 SNSGELEM

114 35597-2-255 1 SNSGELEM

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 458

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SERVICE BULLETIN

References

Fig. A-FBJAA

Installation of the New Sensing

Elements between FR44 and FR50 on

LH side

Sheet 01

Sheet 02

Sheet 03

Sheet 04

(a) Install the sensing elements and the supports between FR44 and FR46.

1 Install the supports between FR44 and FR46 :

1 Support F3611549600000 Item 81

17 Clamp NSA5543-00 Item 10

9 Spacer NSA5527-03-01 Item 16

3 Spacer NSA5527-03-11 Item 18

21 Washer ASNA2397-10L Item 14

2 Bolt NAS6603-24 Item 19

5 Bolt NAS6603-1 Item 20

7 Bolt NAS6603-9 Item 21

1 Bolt NAS6603-16 Item 23

2 Bolt NAS6603-2 Item 29

2 Install the placards at FR44 :

1 Placard F1131031621800 Item 34

1 Placard F1131031623800 Item 35

1 Placard F1131031623900 Item 36

1 Placard F1131031621900 Item 37

3 Install the sensing elements between FR44 and FR46 :

FIN 99HF

1 Sensing Element 35618-2-255 Item 103

FIN 304HF

1 Sensing Element 35618-2-255 Item 103

34 Sleeve-Protective NSA5539S Item 13

4 Nut NSA5542-00 Item 15

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 459

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@A340

SERVICE BULLETIN

(b) Install the sensing elements and the supports between FR46 and FR50.

1 Install the supports between FR46 and FR50 :

2 Angle NSA5546-00 Item 30

4 Rivet-Blind ASNA0342T04-01 Item 11

1 Support F3611549500000 Item 80

4 Support F3611549100000 Item 79

12 Clamp NSA5543-00 Item 10

2 Spacer NSA5527-03-01 Item 16

1 Spacer NSA5527-03-10 Item 17

14 Washer ASNA2397-10L Item 14

9 Bolt NAS6603-1 Item 20

2 Bolt NAS6603-9 Item 21

1 Bolt NAS6603-32 Item 26

6 Bolt NAS6603-2 Item 29

2 Install the placards between FR46 and FR50 :

1 Placard F1131031623900 Item 36

1 Placard F1131031621900 Item 37

2 Placard F1131031624000 Item 38

2 Placard F1131031622000 Item 39

1 Placard F1131031622100 Item 40

1 Placard F1131031624100 Item 41

3 Install the sensing elements between FR46 and FR50 :

FIN 100HF

1 Sensing Element 35597-2-255 Item 114

FIN 305HF

1 Sensing Element 35598-2-255 Item 105

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 460

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SERVICE BULLETIN

24 Sleeve-Protective NSA5539S Item 13

4 Nut NSA5542-00 Item 15

NOTE: Secure the nuts Item 15 with wire-lock MS20995C32 Item 27.

(17) Subtask 364033-831-011-001 - Install the sensing elements and the supports

between FR50 and FR53.6.

Work Zones and Access Panels

Zone Access/Work location

190 Work location from Frame 50 to Frame 53.6

Manpower Resources

Manhours 21.00

Minimum number of person 1

Subtask elapsed time 21.00

Skills AIRFRAME

Material necessary to do the job

Kit 364033A01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

10 NSA5543-00 37 CLAMP

11 ASNA0342T04-01 6 BOLT

13 NSA5539S 74 SLEEVE

14 ASNA2397-10L 51 WASHER

15 NSA5542-00 6 NUT

16 NSA5527-03-01 16 SPACER

18 NSA5527-03-11 1 SPACER

20 NAS6603-1 23 BOLT

21 NAS6603-9 16 BOLT

22 NSA5527-03-15 1 SPACER

24 NAS6603-15 1 BOLT

25 NSA5545-00 1 ANGLE

28 NAS6603-12 1 BOLT

29 NAS6603-2 10 BOLT

30 NSA5546-00 2 ANGLE

40 F1131031622100 1 PLACARD

41 F1131031624100 1 PLACARD

42 F1131031622200 2 PLACARD

43 F1131031624200 2 PLACARD

44 F1131031620400 2 PLACARD

45 F1131031624300 2 PLACARD

70 F3611548300000 1 SUPPORT

72 F3611548700000 1 SUPPORT

73 F3611548500000 1 SUPPORT

74 F3611548900000 1 SUPPORT

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 461

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SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

75 F3611548400000 1 SUPPORT

76 F3611548200000 1 SUPPORT

77 F3611548620000 1 SUPPORT

79 F3611549100000 3 SUPPORT

82 F3611549400000 1 SUPPORT

83 F3611549800000 1 SUPPORT

84 F3611549300000 1 SUPPORT

104 35567-3-255 1 SNSGELEM

106 35595-2-255 3 SNSGELEM

107 35596-2-255 1 SNSGELEM

108 35568-4-255 1 SNSGELEM

References

Fig. A-FBKAA

Installation of the New Sensing

Elements between FR50 and FR53.6 on

LH side

Sheet 01

Sheet 02

Sheet 03

Sheet 04

(a) Install the sensing elements and the supports between FR50 and FR53.2.

1 Install the supports between FR50 and FR53.2 :

1 Support F3611548700000 Item 72

1 Support F3611548400000 Item 75

1 Support F3611549400000 Item 82

1 Angle NSA5546-00 Item 30

2 Rivet-Blind ASNA0342T04-01 Item 11

13 Clamp NSA5543-00 Item 10

7 Spacer NSA5527-03-01 Item 16

16 Washer ASNA2397-10L Item 14

9 Bolt NAS6603-1 Item 20

7 Bolt NAS6603-9 Item 21

2 Install the placards between FR50 and FR53.2 :

1 Placard F1131031622100 Item 40

1 Placard F1131031624100 Item 41

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 462

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@A340

SERVICE BULLETIN

1 Placard F1131031622200 Item 42

1 Placard F1131031624200 Item 43

3 Install the sensing elements between FR50 and FR53.2 :

FIN 101HF

1 Sensing Element 35595-2-255 Item 106

FIN 306HF

1 Sensing Element 35595-2-255 Item 106

26 Sleeve-Protective NSA5539S Item 13

2 Nut NSA5542-00 Item 15

NOTE: Secure the nuts Item 15 with wire-lock MS20995C32 Item 27.

(b) Install the sensing elements and the supports between FR53.2 and FR53.6.

1 Install the supports between FR53.2 and FR53.6 :

1 Support F3611548300000 Item 70

1 Support F3611548500000 Item 73

1 Support F3611548900000 Item 74

1 Support F3611548200000 Item 76

1 Support F3611548620000 Item 77

3 Support F3611549100000 Item 79

1 Support F3611549800000 Item 83

1 Support F3611549300000 Item 84

1 Angle NSA5545-00 Item 25

1 Angle NSA5546-00 Item 30

4 Rivet-Blind ASNA0342T04-01 Item 11

24 Clamp NSA5543-00 Item 10

9 Spacer NSA5527-03-01 Item 16

1 Spacer NSA5527-03-11 Item 18

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 463

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SERVICE BULLETIN

1 Spacer NSA5527-03-15 Item 22

35 Washer ASNA2397-10L Item 14

14 Bolt NAS6603-1 Item 20

9 Bolt NAS6603-9 Item 21

1 Bolt NAS6603-15 Item 24

1 Bolt NAS6603-12 Item 28

10 Bolt NAS6603-2 Item 29

2 Install the placards between FR53.2 and FR53.6 :

1 Placard F1131031622200 Item 42

1 Placard F1131031624200 Item 43

2 Placard F1131031620400 Item 44

2 Placard F1131031624300 Item 45

3 Install the sensing elements between FR53.2 and FR53.6 :

FIN 102HF

1 Sensing Element 35595-2-255 Item 106

FIN 307HF

1 Sensing Element 35596-2-255 Item 107

FIN 23HF

1 Sensing Element 35568-4-255 Item 108

FIN 308HF

1 Sensing Element 35567-3-255 Item 104

48 Sleeve-Protective NSA5539S Item 13

4 Nut NSA5542-00 Item 15

NOTE: Secure the nuts Item 15 with wire-lock MS20995C32 Item 27.

(18) Subtask 364033-831-012-001 - Install the sensing elements and the supports

between FR53.6 and FR55.

Work Zones and Access Panels

Zone Access/Work location

190 Work location from Frame 53.6 to Frame 55

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 464

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SERVICE BULLETIN

Manpower Resources

Manhours 14.00

Minimum number of person 1

Subtask elapsed time 14.00

Skills AIRFRAME

Material necessary to do the job

Kit 364033A01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

10 NSA5543-00 27 CLAMP

11 ASNA0342T04-01 2 BOLT

13 NSA5539S 55 SLEEVE

14 ASNA2397-10L 32 WASHER

15 NSA5542-00 2 NUT

16 NSA5527-03-01 6 SPACER

17 NSA5527-03-10 2 SPACER

18 NSA5527-03-11 5 SPACER

20 NAS6603-1 17 BOLT

21 NAS6603-9 1 BOLT

26 NAS6603-32 2 BOLT

29 NAS6603-2 2 BOLT

30 NSA5546-00 1 ANGLE

70 F3611548300000 1 SUPPORT

79 F3611549100000 1 SUPPORT

85 NSA5549-90 2 CONNECTR

86 NSA5538-00 3 CLAMP

87 NAS6603-17 5 BOLT

88 F1131031620500 1 PLACARD

89 F1131031624400 1 PLACARD

90 F1131031620600 1 PLACARD

91 F1131031624500 1 PLACARD

93 F3611549200095 1 SUPPORT

94 NAS6603-10 5 BOLT

95 F3611549000000 1 SUPPORT

109 35597-3-255 1 SNSGELEM

110 35587-2-255 1 SNSGELEM

111 35627-2-255 1 SNSGELEM

112 35625-2-255 1 SNSGELEM

References

Fig. A-FBLAA

Installation of the New Sensing

Elements between FR53.6 and FR55 on

LH side

Sheet 01

Sheet 02

Sheet 03

Sheet 04

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 465

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@A340

SERVICE BULLETIN

(a) Install the sensing elements and the supports between FR53.6 and FR55.

1 Install the supports between FR53.6 and FR55 :

1 Support F3611548300000 Item 70

1 Support F3611549100000 Item 79

1 Support F3611549200095 Item 93

1 Support F3611549000000 Item 95

1 Angle NSA5546-00 Item 30

2 Rivet-Blind ASNA0342T04-01 Item 11

27 Clamp NSA5543-00 Item 10

3 Clamp NSA5538-00 Item 86

6 Spacer NSA5527-03-01 Item 16

2 Spacer NSA5527-03-10 Item 17

5 Spacer NSA5527-03-11 Item 18

32 Washer ASNA2397-10L Item 14

17 Bolt NAS6603-1 Item 20

1 Bolt NAS6603-9 Item 21

2 Bolt NAS6603-32 Item 26

2 Bolt NAS6603-2 Item 29

5 Bolt NAS6603-17 Item 87

5 Bolt NAS6603-10 Item 94

2 Install the placards between FR53.6 and FR55 :

1 Placard F1131031620500 Item 88

1 Placard F1131031624400 Item 89

1 Placard F1131031620600 Item 90

1 Placard F1131031624500 Item 91

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 466

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@A340

SERVICE BULLETIN

3 Install the sensing elements between FR53.6 and FR55 :

FIN 24HF

1 Sensing Element 35597-3-255 Item 109

FIN 311HF

1 Sensing Element 35587-2-255 Item 110

FIN 25HF

1 Sensing Element 35627-2-255 Item 111

FIN 312HF

1 Sensing Element 35625-2-255 Item 112

2 Nut NSA5542-00 Item 15

2 Connector NSA5549-90 Item 85

55 Sleeve-Protective NSA5539S Item 13

NOTE: Secure the nuts Item 15 with wire-lock MS20995C32 Item 27.

(19) Subtask 364033-010-004-001 - If necessary, remove the ducts between FR39 and

FR40 for access.

Work Zones and Access Panels

Zone Access/Work location

190

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills AIRFRAME

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-010-801

Fig. A-FBPAA

Removal/Installation of the Ducts

Between FR39 and FR40 for Access

Sheet 01

(a) Remove :

Fig. A-FBPAA

(Refer to AMM Task 21-20-00-010-801)

1 Duct assy Item (125) Retain

1 Duct assy Item (126) Retain

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 467

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SERVICE BULLETIN

1 Duct assy Item (127) Retain

(20) Subtask 364033-831-013-001 - Install the new supports for the new harness

between FR39.1 and FR39.2.

Work Zones and Access Panels

Zone Access/Work location

190

Manpower Resources

Manhours 3.00

Minimum number of person 1

Subtask elapsed time 3.00

Skills AIRFRAME

Material necessary to do the job

Kit 364033A01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

63 ASNA2327-3-8 2 SUPPORT

64 F5391094700095 1 PLATE

65 NSA5456-3-8 1 SUPPORT

97 ASNA2050DCJ3215 14 RIVET

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Corrosion Inhibiting Brush

Consistency

09-013B As required

References

Fig. A-FBNAA

Installation of the Supports for the New

Harness

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

(a) At FR39.1, remove a support between STGR 37 and STGR 38.

Fig. A-FBNAA Sheet 02 and Fig. A-FBNAA Sheet 03

1 Remove :

2 Rivet Item (97) Discard

1 Support Item (88) Retain

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 468

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SERVICE BULLETIN

2 Install :

2 Rivet ASNA2050DCJ3215 Item 97

NOTE: Wet install the fasteners with :

Corrosion Inhibiting

Brush Consistency

09-013B As required

(b) At FR39.1, install a support between STGR 37 and STGR 38.

Fig. A-FBNAA Sheet 02 and Fig. A-FBNAA Sheet 03

1 Put the support Item (88) in position as shown on Fig. A-FBNAA Sheet 03.

2 Drill two holes on the structure to a diameter comprised between 3.25mm

(0.128in.) and 3.35mm (0.132in.) to match the holes of the support Item (88).

3 Install :

1 Support Item (88) Retained at

removal

2 Rivet ASNA2050DCJ3215 Item 97

NOTE: Wet install the fasteners with :

Corrosion Inhibiting

Brush Consistency

09-013B As required

(c) At FR39.2, install a plate between STGR 46 and STGR 47.

Fig. A-FBNAA Sheet 02 and Fig. A-FBNAA Sheet 04

1 Remove :

2 Rivet Item (97) Discard

1 Support Item (89) Retain

2 Put the plate Item 64 in position as shown on Fig. A-FBNAA Sheet 04.

3 Drill one hole on the plate Item 64 to a diameter comprised between 3.25mm

(0.128in.) and 3.35mm (0.132in.) to match the hole of the structure.

4 Drill three holes on the structure to a diameter comprised between 3.25mm

(0.128in.) and 3.35mm (0.132in.) to match the holes of the plate Item (64).

5 Install :

1 Plate F5391094700095 Item 64

4 Rivet ASNA2050DCJ3215 Item 97

NOTE: Wet install the fasteners with :

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 469

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SERVICE BULLETIN

Corrosion Inhibiting

Brush Consistency

09-013B As required

(d) At FR39.2, install two supports between STGR46 and STGR48.

Fig. A-FBNAA Sheet 02 and Fig. A-FBNAA Sheet 04

1 Put the supports Item 63 in position as shown on Fig. A-FBNAA Sheet 04.

2 Drill four holes on the structure to a diameter comprised between 3.25mm

(0.128in.) and 3.35mm (0.132in.) to match the holes of the supports Item 63.

3 Install :

2 Support ASNA2327-3-8 Item 63

4 Rivet ASNA2050DCJ3215 Item 97

NOTE: Wet install the fasteners with :

Corrosion Inhibiting

Brush Consistency

09-013B As required

(e) At FR39.1, install a support between STGR 39 and STGR 40.

Fig. A-FBNAA Sheet 02 and Fig. A-FBNAA Sheet 05

1 Put the support Item 65 in position as shown on Fig. A-FBNAA Sheet 05.

2 Drill two holes on the structure to a diameter comprised between 3.25mm

(0.128in.) and 3.35mm (0.132in.) to match the holes of the support Item 65.

3 Install :

1 Support NSA5456-3-8 Item 65

2 Rivet ASNA2050DCJ3215 Item 97

NOTE: Wet install the fasteners with :

Corrosion Inhibiting

Brush Consistency

09-013B As required

(21) Subtask 364033-831-014-001 - Install the Interconnecting Electrical Wire FIN 309HF

and 310HF, between the sensing elements.

Work Zones and Access Panels

Zone Access/Work location

150

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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Manpower Resources

Manhours 3.00

Minimum number of person 1

Subtask elapsed time 3.00

Skills NON SPECIFIC

Material necessary to do the job

Kit 364033A02R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

14 ASNA2397-10L 1 WASHER

18 NSA5527-03-11 1 SPACER

92 NSA57304-643ADL 1 PLATE

155 NSA5516-04ND 1 CLAMP

168 NAS1801-3-22 1 SCREW

169 NSA935401-03 8 TIE

174 35301-74 1 CABLE

175 35301-75 2 CABLE

182 NSA5050-4 1 NUT

F1131031521900 1 PLACARD

F1131031522000 1 PLACARD

F9000095227895 BUNDLE

F9100095005595 1 PLACARD

References

Fig. A-FBCAA

Drilling of a New Hole in the Structure

between FR53.5 and FR53.6 on the LH

side and Installation of Sensing

Elements

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Fig. A-FCCAA

Installation of the Wiring of the New

Sensing Elements

Sheet 01

Sheet 02

(a) Put in position :

FIN 309HF

1 Cable-Electrical

Interconnecting

35301-74 Item 174

(b) Put in position :

FIN 310HF

1 Cable-Electrical

Interconnecting

35301-75 Item 175

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(c) Install the splice FIN 3593VS (PN E0360RK1816) between the FIN 309HF and the

FIN 310HF, supplied in :

Bundle F9000095227895

(d) Identify the splice FIN 3593VS with the identification sleeves and the identification

label supplied in :

1 Placard F9100095005595

and

Bundle F9000095227895

(e) On the fuselage close to the plugs, identify the FIN 309HF and the FIN 310HF with

:

1 Placard F1131031521900

and

1 Placard F1131031522000

(f) Identify the wire No. 3622-0543 of the FIN 310HF and the wire No. 3622-0544 of

the FIN 309HF with the identification sleeves supplied in :

1 Placard F9100095005595

(g) Modify the splice FIN 3503VS :

1 Before any disconnection, record the wires number associated to the FIN

137HF and the FIN 138HF.

2 Remove the splice FIN 3503VS between the FIN 137HF and the FIN 138HF :

FIN 3503VS

1 Splice Discard

NOTE: Retain the identification sleeves and the identification label of

the 3503VS and of the wires associated to the FIN 137HF and

the FIN 138HF.

3 Remove :

FIN 137HF

1 Cable-Electrical

Interconnecting

35301-74 Item (174) Discard

4 Maintain in position :

FIN 138HF

1 Cable-Electrical

Interconnecting

35301-75 Item (175)

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5 Put in position :

FIN 137HF

1 Cable-Electrical

Interconnecting

35301-75 Item 175

6 Install the new splice FIN 3503VS (PN E0360RK1816) between the FIN

137HF and the FIN 138HF, supplied in :

Bundle F9000095227895

NOTE: Identify the splice FIN 3503VS with the identification sleeves

and the identification label retained at removal.

NOTE: In accordance to the wires connections recorded at removal,

identify the wires associated to the FINs 137HF and 138HF

with the retained identification sleeves.

(h) Between Frame 53.5 and Frame 53.6 and as shown in Fig. A-FBCAA Sheet 01 and

Fig. A-FBCAA Sheet 03, install the FINs 137HF and 138HF and the FINs 309HF

and 310HF (spliced previously) with :

1 Spacer NSA5527-03-11 Item 18

1 Clamp NSA5516-04ND Item (155) Retained at

removal

1 Clamp NSA5516-04ND Item 155

1 Washer ASNA2397-10L Item 14

1 Screw NAS1801-3-22 Item 168

and attach it with :

8 Tie-Cable NSA935401-03 Item 169

NOTE: After connection, secure the FINs 137HF and 138HF and the FINs

309HF and 310HF with Wire-lock MS20995C32 item 27, (Refer to

Fig. A-FBCAA Sheet 05).

(i) Secure the FIN 310HF :

Refer to Fig. A-FBCAA Sheet 04

1 Remove :

1 Nut Discard

2 Install :

1 Plate-Attachment NSA57304-643ADL Item 92

With :

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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1 Nut NSA5050-4 Item 182

3 Secure the new nut and the FIN 310HF with wire-lock MS20995C32 item 27,

(Refer to Fig. A-FBCAA Sheet 05).

(22) Subtask 364033-831-015-001 - Install the new Harness 2SG.

Work Zones and Access Panels

Zone Access/Work location

190

Manpower Resources

Manhours 26.00

Minimum number of person 2

Subtask elapsed time 13.00

Skills NON SPECIFIC

Material necessary to do the job

Kit 364033A02R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

14 ASNA2397-10L 4 WASHER

16 NSA5527-03-01 2 SPACER

18 NSA5527-03-11 1 SPACER

22 NSA5527-03-15 1 SPACER

131 NSA935808-03 24 WASHER

134 NSA935807-16 1 CLAMP

135 NSA935807-20 1 CLAMP

141 NSA5527-03-02 3 SPACER

150 NSA935807-04 30 CLAMP

151 NSA5159-17 19 STUD

152 NSA5527-03-08 19 SPACER

153 NSA935808-01 13 WASHER

154 NSA5050-3 28 NUT

157 NSA5159-10 1 STUD

158 NAS1801-3-9 4 SCREW

159 NAS1801-3-8 2 SCREW

163 NSA5159-27 5 STUD

165 NSA5527-03-05 1 SPACER

166 NAS1801-3-12 4 SCREW

167 NAS1801-3-10 3 SCREW

170 MS21042-3 4 NUT

171 NAS1801-3-17 2 SCREW

172 NAS1149F0332P 2 WASHER

173 NSA5527-03-12 6 SPACER

174 35301-74 1 CABLE

176 NSA5516-21ND 5 CLAMP

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SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

177 NSA5516-22ND 5 CLAMP

178 NSA5516-23ND 5 CLAMP

179 NSA5516-07ND 2 CLAMP

180 NSA5516-08ND 2 CLAMP

181 NSA5516-10ND 2 CLAMP

183 NSA934710E20 3 SPRING

184 NSA934710T11 2 FITTING

E0432A04 20 (M) CONDUIT

F1131031522100 1 PLACARD

F9000095227895 BUNDLE

References

Elec. Std. Practices Manual (ESPM) 20-43-42

Fig. A-FBMAA

Installation of the New Harness 2SG

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

Sheet 09

Sheet 10

Sheet 11

Sheet 12

Sheet 13

Sheet 14

Sheet 15

Sheet 16

Sheet 17

Sheet 18

Sheet 19

Sheet 20

Sheet 21

Sheet 22

Fig. A-FCCAA

Installation of the Wiring of the New

Sensing Elements

Sheet 01

Sheet 02

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(a) Install supports of new routing between 302HF located on the left hand side at

stringer 36 and Frame 40 and the 3520VP located on the right hand side at Frame

39.1 :

1 On the left hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03, Fig. A-FBMAA Sheet 04, Fig. A-FBMAA Sheet 05 and Fig. AFBMAA Sheet 06, along the Frame 39.1 and between Frame 39.1 and Frame

39.2, remove :

a For Section A-A :

7 Screw Item (130) Discard

7 Washer Item (131) Discard

7 Clamp Item (150) Retain

2 On the left hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03, Fig. A-FBMAA Sheet 04, Fig. A-FBMAA Sheet 05 and Fig. AFBMAA Sheet 06, along the Frame 39.1 and between Frame 39.1 and Frame

39.2, install :

a For Section B-B :

7 Stud NSA5159-17 Item 151

7 Clamp Item (150) Retained at

removal

7 Spacer NSA5527-03-08 Item 152

7 Clamp NSA935807-04 Item 150

7 Washer NSA935808-03 Item 131

7 Nut NSA5050-3 Item 154

b For Section C-C :

1 Stud NSA5159-17 Item 151

1 Clamp NSA935807-04 Item 150

1 Spacer NSA5527-03-08 Item 152

1 Clamp NSA935807-04 Item 150

1 Washer NSA935808-03 Item 131

1 Nut NSA5050-3 Item 154

NOTE: Install this hardware on the support Item 65 installed

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previously.

3 On the left hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03, Fig. A-FBMAA Sheet 04, Fig. A-FBMAA Sheet 05 , Fig. A-FBMAA

Sheet 07, Fig. A-FBMAA Sheet 08 and Fig. A-FBMAA Sheet 09, along the

Frame 39.1 and between Stringer 39 and 40, remove :

a For Section F-F :

1 Screw Item (130) Discard

1 Washer Item (131) Discard

1 Clamp Item (150) Retain

b For Section G-G :

1 Screw Item (132) Discard

1 Washer Item (133) Discard

1 Clamp Item (155) Retain

4 On the left hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03, Fig. A-FBMAA Sheet 04, Fig. A-FBMAA Sheet 05 , Fig. A-FBMAA

Sheet 07, Fig. A-FBMAA Sheet 08 and Fig. A-FBMAA Sheet 09, along the

Frame 39.1 and between Stringer 39 and 40, install :

a For Section H-H :

1 Stud NSA5159-17 Item 151

1 Clamp Item (150) Retained at

removal

1 Spacer NSA5527-03-08 Item 152

1 Clamp NSA935807-04 Item 150

1 Washer NSA935808-03 Item 131

1 Nut NSA5050-3 Item 154

b For Section J-J :

1 Stud NSA5159-17 Item 151

1 Clamp Item (155) Retained at

removal

1 Spacer NSA5527-03-08 Item 152

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1 Clamp NSA935807-04 Item 150

1 Washer NSA935808-03 Item 131

1 Nut NSA5050-3 Item 154

5 On the left hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 09, along the Frame 39.1 and between

Stringer 40 and 43, remove for detail F :

2 Screw Item (136) Discard

2 Washer Item (137) Discard

2 Clamp Item (135) Retain

2 Clamp Item (134) Retain

6 On the left hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 09, along the Frame 39.1 and between

Stringer 40 and 43, install for detail G :

2 Stud NSA5159-17 Item 151

2 Clamp Item (134) Retained at

removal

2 Clamp Item (135) Retained at

removal

2 Spacer NSA5527-03-08 Item 152

2 Clamp NSA935807-04 Item 150

2 Washer NSA935808-03 Item 131

2 Nut NSA5050-3 Item 154

7 On the left hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03, Fig. A-FBMAA Sheet 10 and Fig. A-FBMAA Sheet 11, along the

Frame 39.1 and between Stringers 44 and 45, remove :

a For Section K-K :

1 Nut Item (154) Discard

1 Washer Item (153) Discard

1 Clamp Item (138) Retain

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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SERVICE BULLETIN

1 Spacer Item (152) Retain

1 Clamp Item (135) Retain

1 Clamp Item (134) Retain

1 Stud Item (151) Retain

Or

1 Nut Item (154) Discard

1 Washer Item (153) Discard

1 Clamp Item (138) Retain

1 Clamp Item (139) Retain

1 Spacer Item (152) Discard

1 Clamp Item (135) Retain

1 Clamp Item (134) Retain

1 Stud Item (151) Discard

8 On the left hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03, Fig. A-FBMAA Sheet 10 and Fig. A-FBMAA Sheet 11, along the

Frame 39.1 and between Stringers 44 and 45, install :

a For Section M-M :

1 Stud Item (151) Retained at

removal

1 Clamp Item (134) Retained at

removal

1 Clamp Item (135) Retained at

removal

1 Spacer Item (152) Retained at

removal

1 Clamp Item (138) Retained at

removal

1 Clamp NSA935807-04 Item 150

1 Washer NSA935808-03 Item 131

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1 Nut NSA5050-3 Item 154

Or

1 Stud NSA5159-27 Item 163

1 Clamp Item (134) Retained at

removal

1 Clamp Item (135) Retained at

removal

2 Spacer NSA5527-03-12 Item 173

1 Clamp Item (139) Retained at

removal

1 Clamp Item (138) Retained at

removal

1 Clamp NSA935807-04 Item 150

1 Washer NSA935808-03 Item 131

1 Nut NSA5050-3 Item 154

9 On the left hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03, Fig. A-FBMAA Sheet 10 and Fig. A-FBMAA Sheet 12, along the

Frame 39.1 and between Stringers 44 and 45, remove :

a For Section L-L :

1 Screw Item (130) Discard

1 Washer Item (153) Discard

1 Clamp Item (135) Retain

1 Clamp Item (134) Retain

10 On the left hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03, Fig. A-FBMAA Sheet 10 and Fig. A-FBMAA Sheet 12, along the

Frame 39.1 and between Stringers 44 and 45, install :

a For Section N-N :

1 Stud NSA5159-17 Item 151

1 Clamp Item (134) Retained at

removal

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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1 Clamp Item (135) Retained at

removal

1 Spacer NSA5527-03-08 Item 152

1 Clamp NSA935807-04 Item 150

1 Washer NSA935808-03 Item 131

1 Nut NSA5050-3 Item 154

11 On the left hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03, Fig. A-FBMAA Sheet 13 and Fig. A-FBMAA Sheet 14, along the

Frame 39.1 and between Stringers 46 and 48, remove :

a For Section P-P :

1 Nut Item (154) Discard

1 Washer Item (153) Discard

1 Clamp Item (139) Retain

1 Spacer Item (152) Retain

1 Clamp Item (135) Retain

1 Clamp Item (134) Retain

1 Stud Item (151) Discard

Or

1 Nut Item (154) Discard

1 Washer Item (153) Discard

1 Clamp Item (138) Retain

1 Clamp Item (139) Retain

1 Spacer Item (152) Discard

1 Clamp Item (135) Retain

1 Clamp Item (134) Retain

1 Stud Item (151) Discard

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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12 On the left hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03, Fig. A-FBMAA Sheet 13 and Fig. A-FBMAA Sheet 14, along the

Frame 39.1 and between Stringers 46 and 48, install :

a For Section R-R :

1 Stud NSA5159-17 Item 151

1 Clamp Item (134) Retained at

removal

1 Clamp Item (135) Retained at

removal

1 Spacer Item (152) Retained at

removal

1 Clamp Item (139) Retained at

removal

1 Clamp NSA935807-04 Item 150

1 Washer NSA935808-03 Item 131

1 Nut NSA5050-3 Item 154

Or

1 Stud NSA5159-27 Item 163

1 Clamp Item (134) Retained at

removal

1 Clamp Item (135) Retained at

removal

2 Spacer NSA5527-03-12 Item 173

1 Clamp Item (139) Retained at

removal

1 Clamp Item (138) Retained at

removal

1 Clamp NSA935807-04 Item 150

1 Washer NSA935808-03 Item 131

1 Nut NSA5050-3 Item 154

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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13 On the left hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03, Fig. A-FBMAA Sheet 13 and Fig. A-FBMAA Sheet 15, along the

Frame 39.1 and between Stringers 46 and 48, remove :

a For Section Q-Q :

1 Nut Item (154) Discard

1 Washer Item (153) Discard

1 Clamp Item (135) Retain

1 Spacer Item (152) Retain

1 Clamp Item (134) Retain

1 Clamp Item (139) Retain

1 Stud Item (151) Retain

Or

1 Nut Item (154) Discard

1 Washer Item (153) Discard

1 Clamp Item (138) Retain

1 Clamp Item (135) Retain

1 Spacer Item (152) Discard

1 Clamp Item (134) Retain

1 Clamp Item (139) Retain

1 Stud Item (144) Discard

14 On the left hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03, Fig. A-FBMAA Sheet 13 and Fig. A-FBMAA Sheet 15, along the

Frame 39.1 and between Stringers 46 and 48, install :

a For Section S-S :

1 Stud Item (151) Retained at

removal

1 Clamp NSA935807-04 Item 150

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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SERVICE BULLETIN

1 Clamp Item (134) Retained at

removal

1 Spacer Item (152) Retained at

removal

1 Clamp Item (139) Retained at

removal

1 Clamp Item (135) Retained at

removal

1 Washer NSA935808-01 Item 153

1 Nut NSA5050-3 Item 154

Or

1 Stud NSA5159-27 Item 163

1 Clamp NSA935807-04 Item 150

1 Clamp Item (134) Retained at

removal

2 Spacer NSA5527-03-12 Item 173

1 Clamp Item (139) Retained at

removal

1 Clamp Item (138) Retained at

removal

1 Clamp Item (135) Retained at

removal

1 Washer NSA935808-01 Item 153

1 Nut NSA5050-3 Item 154

15 On the left hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 16, along the Frame 39.1 and between

Stringers 49 and 52, remove for detail K :

2 Screw Item (132) Discard

2 Washer Item (153) Discard

2 Clamp Item (138) Retain

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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16 On the left hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 16, along the Frame 39.1 and between

Stringers 49 and 52, install for detail L :

2 Stud NSA5159-17 Item 151

2 Clamp Item (138) Retained at

removal

2 Spacer NSA5527-03-08 Item 152

2 Clamp NSA935807-04 Item 150

2 Washer NSA935808-03 Item 131

2 Nut NSA5050-3 Item 154

17 On the left hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 17, along the Frame 39.1 and between

Stringers 52 and 54, remove for Section T-T :

1 Nut Item (154) Discard

1 Washer Item (153) Discard

1 Clamp Item (138) Retain

1 Spacer Item (141) Retain

1 Clamp Item (138) Retain

1 Stud Item (140) Retain

18 On the left hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 17, along the Frame 39.1 and between

Stringers 52 and 54, install for Section U-U :

1 Stud Item (140) Retained at

removal

1 Clamp Item (138) Retained at

removal

1 Spacer Item (141) Retained at

removal

1 Clamp Item (138) Retained at

removal

1 Clamp NSA935807-04 Item 150

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 485

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SERVICE BULLETIN

1 Washer NSA935808-03 Item 131

1 Nut NSA5050-3 Item 154

19 On the right hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 18, along the Frame 39.1 and near the

Stringers 54, remove for detail N :

1 Screw Item (142) Discard

1 Washer Item (153) Discard

1 Clamp Item (138) Retain

20 On the right hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 18, along the Frame 39.1 and near the

Stringers 54, install for detail P :

1 Stud NSA5159-17 Item 151

1 Clamp Item (138) Retained at

removal

1 Spacer NSA5527-03-08 Item 152

1 Clamp NSA935807-04 Item 150

1 Washer NSA935808-03 Item 131

1 Nut NSA5050-3 Item 154

21 On the right hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 18, along the Frame 39.1 and between

Stringers 54 and 48, remove for detail Q :

3 Screw Item (142) Discard

3 Washer Item (153) Discard

3 Clamp Item (138) Retain

22 On the right hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 18, along the Frame 39.1 and between

Stringers 54 and 48, install for detail R :

3 Clamp NSA935807-04 Item 150

3 Clamp Item (138) Retained at

removal

3 Washer NSA935808-01 Item 153

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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3 Screw NAS1801-3-9 Item 158

23 On the right hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 18, between the Frame 39.1 and Frame

39.2 and between Stringers 48 and 46, install for detail S :

2 Clamp NSA935807-04 Item 150

2 Washer NSA935808-03 Item 131

2 Screw NAS1801-3-8 Item 159

NOTE: Install this hardware on the support Item 63 installed

previously.

24 On the right hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 19, between the Frame 39.1 and Frame

39.2 and between Stringers 48 and 46, install for Section W-W :

2 Spacer NSA5527-03-02 Item 141

2 Clamp NSA5516-07ND Item 179

or

2 Clamp NSA5516-08ND Item 180

or

2 Clamp NSA5516-10ND Item 181

and

2 Washer NAS1149F0332P Item 172

2 Screw NAS1801-3-17 Item 171

NOTE: Depends on aircraft configuration, use the PN NSA5516-07ND

or NSA5516-08ND or NSA5516-10ND for Item 170.

NOTE: Install this hardware on the support Item 64 installed

previously.

25 On the right hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 19, between the Frame 39.1 and Frame

39.2 and between Stringers 48 and 46, install for Section V-V :

1 Stud NSA5159-27 Item 163

1 Spacer NSA5527-03-01 Item 16

1 Clamp NSA935807-16 Item 134

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 487

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1 Spacer NSA5527-03-08 Item 152

1 Clamp NSA935807-20 Item 135

1 Washer NSA935808-01 Item 153

1 Nut NSA5050-3 Item 154

NOTE: Install this hardware on the support Item 64 installed

previously.

26 On the right hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 20, between the Frame 39.1 and Frame

39.2 and between Stringers 47 and 46, remove for detail T :

1 Screw Item (136) Discard

1 Washer Item (153) Discard

1 Clamp Item (135) Retain

1 Clamp Item (134) Retain

27 On the right hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 20, between the Frame 39.1 and Frame

39.2 and between Stringers 47 and 46, install for detail U :

1 Stud NSA5159-17 Item 151

1 Spacer NSA5527-03-02 Item 141

1 Clamp Item (134) Retained at

removal

1 Spacer NSA5527-03-05 Item 165

1 Clamp Item (135) Retained at

removal

1 Washer NSA935808-01 Item 153

1 Nut NSA5050-3 Item 154

28 On the right hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 20, between the Frame 39.1 and Frame

39.2 and between Stringers 47 and 46, remove for detail Y :

1 Screw Item (143) Discard

1 Washer Item (133) Discard

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 488

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1 Clamp Item (155) Retain

1 Clamp Item (155) Retain

29 On the right hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 20, between the Frame 39.1 and Frame

39.2 and between Stringers 47 and 46, install for detail Z :

1 Stud NSA5159-27 Item 163

1 Clamp Item (155) Retained at

removal

1 Clamp Item (155) Retained at

removal

1 Spacer NSA5527-03-08 Item 152

1 Spacer NSA5527-03-15 Item 22

1 Clamp NSA935807-04 Item 150

1 Washer NSA935808-03 Item 131

1 Nut NSA5050-3 Item 154

30 On the right hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 20, between the Frame 39.1 and Frame

39.2 and between Stringers 46 and 45, remove for detail W :

1 Screw Item (136) Discard

1 Washer Item (153) Discard

1 Clamp Item (135) Retain

1 Clamp Item (134) Discard

31 On the right hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 20, between the Frame 39.1 and Frame

39.2 and between Stringers 46 and 45, install for detail X :

1 Stud NSA5159-10 Item 157

And

1 Clamp NSA5516-21ND Item 176

Or

1 Clamp NSA5516-22ND Item 177

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 489

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SERVICE BULLETIN

Or

1 Clamp NSA5516-23ND Item 178

And

1 Spacer NSA5527-03-01 Item 16

1 Spacer NSA5527-03-08 Item 152

1 Clamp Item (135) Retained at

removal

1 Washer NSA935808-01 Item 153

1 Nut NSA5050-3 Item 154

NOTE: Depends on aircraft configuration, use the PN NSA5516-21ND

or NSA5516-22ND or NSA5516-23ND for Item 166.

32 On the right hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 21, between the Frame 39.1 and Frame

39.2 and between Stringers 44 and 43, remove for detail AA :

1 Screw Item (136) Discard

1 Washer Item (153) Discard

1 Clamp Item (135) Retain

1 Clamp Item (134) Discard

33 On the right hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 21, between the Frame 39.1 and Frame

39.2 and between Stringers 44 and 43, install for detail AB :

1 Stud NSA5159-17 Item 151

And

1 Clamp NSA5516-21ND Item 176

Or

1 Clamp NSA5516-22ND Item 177

Or

1 Clamp NSA5516-23ND Item 178

And

1 Spacer NSA5527-03-11 Item 18

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 490

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SERVICE BULLETIN

1 Clamp Item (135) Retained at

removal

1 Washer NSA935808-01 Item 153

1 Nut NSA5050-3 Item 154

NOTE: Depends on aircraft configuration, use the PN NSA5516-21ND

or NSA5516-22ND or NSA5516-23ND for Item 166.

34 On the right hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 21, between the Frame 39.1 and Frame

39.2 and between Stringers 42 and 38, remove for detail AC :

3 Screw Item (136) Discard

3 Washer Item (153) Discard

3 Clamp Item (135) Retain

3 Clamp Item (134) Discard

35 On the right hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 21, between the Frame 39.1 and Frame

39.2 and between Stringers 42 and 38, install for detail AD :

3 Clamp NSA5516-21ND Item 176

Or

3 Clamp NSA5516-22ND Item 177

Or

3 Clamp NSA5516-23ND Item 178

And

3 Clamp Item (135) Retained at

removal

3 Washer NSA935808-01 Item 153

3 Screw NAS1801-3-10 Item 167

NOTE: Depends on aircraft configuration, use the PN NSA5516-21ND

or NSA5516-22ND or NSA5516-23ND for Item 166.

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 491

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SERVICE BULLETIN

36 On the right hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 21, along the Frame 39.1 and between

Stringers 38 and 37, remove for detail AE :

1 Screw Item (153) Discard

1 Washer Item (142) Discard

1 Clamp Item (135) Retain

37 On the right hand side, as shown in Fig. A-FBMAA Sheet 02, Fig. A-FBMAA

Sheet 03 and Fig. A-FBMAA Sheet 21, between the Frame 39.1 and Frame

39.2 and between Stringers 38 and 37, install for detail AF :

1 Clamp Item (135) Retained at

removal

1 Washer NSA935808-01 Item 153

1 Screw NAS1801-3-9 Item 158

NOTE: Install this hardware on the support Item (88) installed

previously.

(b) Install the new route 2SG between FIN 302HF located on the left hand side at

stringer 36 and Frame 40 and the FIN 3520VC located in the avionics compartment

:

1 Remove the pressure seal 3520VP :

Refer to ESPM 20-43-42 and to Fig. A-FBMAA Sheet 22

a Remove :

2 Fitting-Seal NSA934710T11 Item (184) Discard

And

3 Spring NSA934710E20 Item (183) Discard

Attached with :

4 Screw NAS1801-3-12 Item (166) Discard

4 Washer ASNA2397-10L Item (14) Discard

4 Nut MS21042-3 Item (170) Discard

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 492

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SERVICE BULLETIN

2 Put in position :

FIN 301HF

1 Cable-Electrical

Interconnecting

35301-74 Item 174

3 Install :

20 (M) Conduit E0432A04

4 Using supports installed at paragraph 3.C.(20).(a), route the wire No.

3622-0540 spliced at paragraph 3.C.(20).(b).2, from FIN 301HF located on the

left hand side at stringer 36 and at Frame 40, through pressure seal 3520VP,

to 3520VC located in avionics compartment as shown in Fig. A-FCCAA Sheet

01 and in Fig. A-FBMAA Sheet 01.

NOTE: The route 2SG rejoins route 2S on the right hand side at

stringer 46 between Frame 39.1 and Frame 39.2 as shown in

Fig. A-FBMAA Sheet 17.

5 Connect the wire No. 3622-0540 as shown on the wiring diagram, Fig. AFCCAA Sheet 01 and as given in the Hook-up Chart lines :

- 1 and 2 (Refer to Fig. A-FCCAA Sheet 02).

NOTE: Use the contacts supplied in :

Bundle F9000095227895

6 Install the splice FIN 3591VS (PN NSA936809RG0002) between the FIN

301HF and the wire No. 3622-0540 supplied in :

Bundle F9000095227895

NOTE: After connection, Secure the FIN 301HF and FIN 302HF with

Wire-lock MS20995C32 item 27.

7 Install the pressure seal 3520VP :

Refer to ESPM 20-43-42 and to Fig. A-FBMAA Sheet 22

a Install :

2 Fitting-Seal NSA934710T11 Item 184

And

3 Spring NSA934710E20 Item 183

Attach with :

4 Screw NAS1801-3-12 Item 166

4 Washer ASNA2397-10L Item 14

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 493

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SERVICE BULLETIN

4 Nut MS21042-3 Item 170

8 Identify the splice FIN 3591VS with the identification sleeves and the

identification label supplied in :

Bundle F9000095227895

9 On the fuselage close to the plugs, identify the FIN 301HF with :

1 Placard F1131031522100

(23) Subtask 364033-831-201-002 - Install the electrical wiring in the FWD cargo

compartment

Work Zones and Access Panels

Zone Access/Work location

130 Work location from Frame 19 to Frame 37.1

Manpower Resources

Manhours 7.50

Minimum number of person 2

Subtask elapsed time 3.50

Skills ELECTRICAL

Material necessary to do the job

Kit 364033D02R04

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

401 F9297000500200 1 EQUIPMNT

402 F9237000207400 1 PLCRDSET

404 NSA935401-03 100 TIE

405 NSA935401-04 100 TIE

406 NSA935401-05 100 TIE

407 NSA935401-10 100 TIE

References

Fig. A-GBAAE

Installation of the Electrical Wiring in the

FWD Cargo Compartment

Sheet 01

Fig. A-GHAAB

Hook-up Chart

Sheet 01

Fig. A-GHBAB

Hook-up Chart

Sheet 01

Fig. A-GWAAE

Wiring Diagram

Sheet 01

Sheet 02

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 494

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SERVICE BULLETIN

(a) Install the electrical wiring in the FWD cargo compartment

1 Install the electrical wires:

Refer to Fig. A-GBAAE Sheet 01

Refer to Fig. A-GHAAB Sheet 01, Line 1 thru 2, END 1,

Refer to Fig. A-GWAAE Sheet 01 thru Fig. A-GWAAE Sheet 02

supplied with:

1 Equipment AssyElectricalF9297000500200 Item 401

2 Attach the electrical wires with:

Refer to Fig. A-GBAAE Sheet 01

100 Tie-Cable NSA935401-03 Item 404

100 Tie-Cable NSA935401-04 Item 405

100 Tie-Cable NSA935401-05 Item 406

100 Tie-Cable NSA935401-10 Item 407

Install the identification placards

1 Placard Set F9237000207400 Item 402

(24) Subtask 364033-831-202-002 - Install the electrical wiring in the AFT cargo

compartment and Bulk cargo compartment

Work Zones and Access Panels

Zone Access/Work location

From 150 Work location Frame 55

To 170 Work location Frame 80

Manpower Resources

Manhours 11.00

Minimum number of person 2

Subtask elapsed time 5.50

Skills ELECTRICAL

Material necessary to do the job

Kit 364033D02R04

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

401 F9297000500200 1 EQUIPMNT

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 495

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ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

402 F9237000207400 1 PLCRDSET

404 NSA935401-03 100 TIE

405 NSA935401-04 100 TIE

406 NSA935401-05 100 TIE

407 NSA935401-10 100 TIE

References

Fig. A-GBBAE

Installation of the Electrical Wiring in the

AFT Cargo Compartment

Sheet 01

Sheet 02

Fig. A-GWAAE

Wiring Diagram

Sheet 01

Sheet 02

Fig. A-GHAAB

Hook-up Chart

Sheet 01

Fig. A-GHBAB

Hook-up Chart

Sheet 01

(a) Install the electrical wiring in the AFT cargo compartment and Bulk cargo

compartment

1 Install the electrical wires on 5866VB between Frame 55 thru Frame 80/82:

Refer to Fig. A-GBBAE Sheet 01

Refer to Fig. A-GWAAE Sheet 01 thru Fig. A-GWAAE Sheet 02

Refer to Fig. A-GHAAB Sheet 01, Line 1 thru 3, END 1,

supplied with:

1 Equipment AssyElectricalF9297000500200 Item 401

2 Attach the electrical wires with:

Refer to Fig. A-GBBAE Sheet 01

100 Tie-Cable NSA935401-03 Item 404

100 Tie-Cable NSA935401-04 Item 405

100 Tie-Cable NSA935401-05 Item 406

100 Tie-Cable NSA935401-10 Item 407

Install the identification placards

1 Placard Set F9237000207400 Item 402

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

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SERVICE BULLETIN

3 Route the electrical wires through the thermal insulator at Frame 80/82:

Refer to Fig. A-GBBAE Sheet 02

1 Insulator-Cable

Protection

ABS0596S006 Item (403)

(25) Subtask 364033-831-203-002 - Modify the electrical wiring in the AFT cargo

compartment, Bulk cargo compartment and Rear fuselage section

Work Zones and Access Panels

Zone Access/Work location

310 Work location from Frame 80/82 to Frame 93

Manpower Resources

Manhours 4.50

Minimum number of person 1

Subtask elapsed time 4.50

Skills ELECTRICAL

References

Fig. A-GBCAE

Preparation for the Electrical Wiring

Installation in the Rear Fuselage Section

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

Sheet 09

Fig. A-GHAAB

Hook-up Chart

Sheet 01

Fig. A-GHBAB

Hook-up Chart

Sheet 01

(a) Remove the pressure seal 5208VP from the pressure Frame at Frame 80/82

Refer to Fig. A-GBCAE Sheet 01 thru Fig. A-GBCAE Sheet 02

Remove:

2 Plate G9249050020000 Item (412) Retain

2 Bulkhead Item (415) Discard

12 Washer Item (417) Discard

4 Washer Item (418) Discard

12 Nut Item (419) Discard

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 497

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SERVICE BULLETIN

4 Screw Item (420) Discard

6 Screw Item (426) Discard

2 Screw Item (427) Discard

(b) Remove the lightning protection of the electrical bundle 5886VB at Frame 90

Refer to Fig. A-GBCAE Sheet 01 thru Fig. A-GBCAE Sheet 07

1 At Frame 90 loosen the electrical receptacle 5215VC, Item (433)

Refer to Fig. A-GBCAE Sheet 03 thru Fig. A-GBCAE Sheet 04

4 Screw Item (430) Discard

4 Washer Item (431) Discard

4 Nut Item (432) Discard

2 Disconnect the electrical wires end from the electrical receptacle 5215VC.

Refer to Fig. A-GBCAE Sheet 03 thru Fig. A-GBCAE Sheet 04

Refer to Fig. A-GHAAB Sheet 01 END 2, Line 9 thru 25,Fig. A-GHBAB Sheet

01 END 2, Line 1 and 7

1 Receptacle Item (433) Retain

3 Remove from Frame 91:

Refer to Fig. A-GBCAE Sheet 03 thru Fig. A-GBCAE Sheet 04

1 Screw Item (314) Discard

1 Washer Item (417) Discard

1 Clamp Item (437) Discard

1 Clip nut Item (353) Discard

4 Remove the lightning protection from the electrical bundle 5886VB at Frame

90.

Fig. A-GBCAE Sheet 03 thru Fig. A-GBCAE Sheet 07

8 Screw Item (314) Discard

12 Washer Item (417) Discard

3 Nut Item (419) Discard

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 498

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SERVICE BULLETIN

21 Clamp Item (437) Retain

3 Spacer Item (442) Retain

1 Clamp Item (443) Retain

4 Screw Item (444) Discard

1 Clip nut Item (448) Discard

or if alternate installed remove:

1 Washer Item (417) Discard

2 Spacer Item (442) Retain

3 Clamp Item (437) Retain

1 Clip nut Item (439) Discard

1 Screw Item (501) Discard

(c) Disconnect the electrical wiring 5865VB from the APU overhead leak detection

system at Frame 93

Refer to Fig. A-GBCAE Sheet 01, Fig. A-GBCAE Sheet 08 thru Fig. A-GBCAE

Sheet 09

Refer to Fig. A-GHAAB Sheet 01

1 Remove between Frame 92 thru Frame 93:

Refer to Fig. A-GBCAE Sheet 08 thru Fig. A-GBCAE Sheet 09

1 Washer Item (417) Discard

1 Nut Item (470) Discard

2 Clamp Item (437) Retain

1 Spacer Item (436) Retain

1 Screw Item (465) Discard

2 Remove from Frame 93:

Refer to Fig. A-GBCAE Sheet 08

2 Washer Item (417) Discard

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 499

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SERVICE BULLETIN

4 Spacer Item (442) Retain

2 Clamp Item (437) Retain

2 Clip nut Item (439) Discard

2 Screw Item (501) Discard

3 Remove the electrical splice 5151VSA from Frame 93:

Refer to Fig. A-GBCAE Sheet 08 thru Fig. A-GBCAE Sheet 09

Refer to Fig. A-GHAAB Sheet 01 END 2, Line 8 and 9

1 Sleeve Item (479) Discard

1 Sleeve Item (480) Discard

1 Splice Item (481) Discard

Refer to Fig. A-GBCAE Sheet 09

1 Washer Item (471) Discard

2 Clamp Item (437) Retain

1 Nut Item (470) Discard

1 Screw Item (464) Discard

(26) Subtask 364033-831-205-001 - Install an additional profile in the Rear fuselage

section

Work Zones and Access Panels

Zone Access/Work location

310 Work location from Frame 90 to Frame 91

Stringer 6RH

Manpower Resources

Manhours 3.00

Minimum number of person 1

Subtask elapsed time 3.00

Skills AIRFRAME

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 500

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SERVICE BULLETIN

Material necessary to do the job

Kit 364033D03R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

314 NAS1801-3-8 2 SCREW

460 F5397083308600 1 SECTION

461 MS21047L3 1 NUT

462 EN6101AD3-08 2 RIVET

463 NAS1149D0332J 2 WASHER

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Corrosion Inhibitive interfay

Sealant

09-005

Corrosion Inhibiting, Fillet

Consistency

09-016 As required

Corrosion Inhibiting low

Adhesion Sealant

09-018

References

Fig. A-GBEAA

Installation of the Bracket between FR90

and FR91

Sheet 01

(a) Install an additional profile in the Rear fuselage section

1 Between Frame 90 thru Frame 91, at RH STGR6, temporarily put into position

Refer to Fig. A-GBEAA Sheet 01

1 Section Assy F5397083308600 Item 460

2 Transfer drill the holes and open holes to final dimension and install:

1 Nut MS21047L3 Item 461

with:

2 Rivet EN6101AD3-08 Item 462

NOTE: For dimensions refer to the table on Fig. A-GBEAA Sheet 01.

3 Between Frame 90 thru Frame 91, at RH STGR6, install:

1 Section Assy F5397083308600 Item 460

with:

2 Screw NAS1801-3-8 Item 314

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 501

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2 Washer NAS1149D0332J Item 463

and protect the surface with:

Corrosion Inhibitive

interfay Sealant

09-005 As required

and

Corrosion Inhibiting,

Fillet Consistency

09-016 As required

, and seal the edges with:

Corrosion Inhibiting

low Adhesion

Sealant

09-018 As required

(27) Subtask 364033-831-204-002 - Install the electrical wiring in the rear fuselage

section

Manpower Resources

Manhours 14.00

Minimum number of person 2

Subtask elapsed time 7.00

Skills ELECTRICAL

Material necessary to do the job

Kit 364033D02R04

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

314 NAS1801-3-8 8 SCREW

320 NSA5527-03-02 5 SPACER

350 AS21919WCH13 6 CLAMP

351 MS21919WCH14 1 CLAMP

352 MS21919WCH8 1 CLAMP

353 NSA5067-3-1 1 NUT

401 F9297000500200 1 EQUIPMNT

402 F9237000207400 6 PLCRDSET

404 NSA935401-03 100 TIE

405 NSA935401-04 100 TIE

406 NSA935401-05 50 TIE

415 NSA934710T14 2 FITTING

416 NAS1801-3-9 8 SCREW

417 NAS1149C0332R 32 WASHER

418 NAS1149D0363K 4 WASHER

419 NAS1291C3M 18 NUT

420 NAS1102-3-10 4 SCREW

423 NAS1801-3-10 2 SCREW

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 502

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SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

426 NAS6703U4 6 BOLT

427 NAS6703U5 2 BOLT

430 NAS1100-04-6 4 SCREW

431 NAS1149CN416R 4 WASHER

432 MS21042-04 4 NUT

439 NSA5066-3-1 1 NUT

444 NAS1801-3-18 3 SCREW

448 NSA5066-3-2 1 NUT

449 NAS1801-08-8 2 SCREW

451 F9249016013200 1 PROTSYS

465 NAS1801-3-15 1 SCREW

469 ASNA0182-4ADL 2 STRIP

470 NAS1291C08M 3 NUT

471 NAS1149CN816R 5 WASHER

472 ASNA0182-3ADL 1 STRIP

475 NAS1801-08-36 2 SCREW

476 NSA5066-08-1 2 NUT

479 E0718-01 0.06 TUBING

480 NSA937210MB0300 0.1 TUBING

481 NSA936809RG0001 2 SPLICE

485 NSA934710E20 3 SPRING

488 E0126-06L 0.2 TUBING

489 F9249016510800 2 PROTSYS

492 ABS0580A17P 1 FITTING

493 NAS1801-3-21 2 SCREW

494 NSA935808C03 2 WASHER

496 NSA5527-03-08D 2 SPACER

501 NAS1801-3-27 2 SCREW

510 E0126-01L 0.35 TUBING

511 F9249016110900 1 PROTSYS

515 AS21919WCH07 1 CLAMP

517 ABS0513-09 1 SUPPORT

518 ABS0520-07P 1 NUT

521 AS21919WCH14 1 CLAMP

528 NAS1801-08-12 1 SCREW

536 AS21919WCH02 3 CLAMP

537 AS21919WCH09 1 CLAMP

843 MS21919WCH12 1 CLAMP

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 503

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References

Fig. A-GBDAE

Installation of the Electrical Wiring in the

Rear Fuselage Section

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

Sheet 09

Sheet 10

(a) Install the electrical wire in the rear fuselage section

1 Install the electrical wire, Item 401, on 5866VB between Frame 80/82 thru

Frame 90

Refer to Fig. A-GBDAE Sheet 01

1 Equipment AssyElectricalF9297000500200 Item 401

Attach the wire with:

2 Placard Set F9237000207400 Item 402

100 Tie-Cable NSA935401-03 Item 404

100 Tie-Cable NSA935401-04 Item 405

50 Tie-Cable NSA935401-05 Item 406

2 Install the electrical wire on 5866VB with the pressure seal 5208VP at Frame

80/82

Refer to Fig. A-GBDAE Sheet 01 thru Fig. A-GBDAE Sheet 02

Install:

2 Plate G9249050020000 Item (412) Retained at

removal

attached with:

2 Fitting-Seal NSA934710T14 Item 415

20 Washer NAS1149C0332R Item 417

4 Washer NAS1149D0363K Item 418

12 Nut NAS1291C3M Item 419

4 Screw NAS1102-3-10 Item 420

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 504

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SERVICE BULLETIN

6 Bolt NAS6703U4 Item 426

2 Bolt NAS6703U5 Item 427

3 Spring NSA934710E20 Item 485

or alternative install:

8 Screw NAS1801-3-9 Item 416

2 Screw NAS1801-3-10 Item 423

3 Install the lightning protection of the electrical bundle 5886VB at Frame 90

Attach to the wires on 5866VB leaving thru the 3 way transition at Frame 90

Refer to Fig. A-GBDAE Sheet 03

0.1 Tubing-Heat-Shrinkable E0126-06L Item 488

NOTE: Cut the sleeve to the necessary length.

4 Route the wires (on 5866VB) between Frame 90 thru Frame 91

Refer to Fig. A-GBDAE Sheet 03 and Fig. A-GBDAE Sheet 08

Install:

1 Protection SystemLightningF9249016510800 Item 489

with:

1 Washer NAS1149C0332R Item 417

1 Screw NAS1801-3-18 Item 444

1 Clamp AS21919WCH13 Item 350

1 Clamp Item (437) Retained at

removal

1 Spacer Item (442) Retained at

removal

5 Route the electrical wires:

Refer to Fig. A-GBDAE Sheet 03 and Fig. A-GBDAE Sheet 07

1 Fitting-Conduit ABS0580A17P Item 492

and install, Item 492, at Frame 90 with:

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 505

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SERVICE BULLETIN

1 Clamp MS21919WCH14 Item 351

2 Nut NAS1291C3M Item 419

1 Strip ASNA0182-4ADL Item 469

2 Screw NAS1801-3-21 Item 493

2 Washer NSA935808C03 Item 494

2 Spacer NSA5527-03-08D Item 496

1 Clamp MS21919WCH12 Item 843

6 Route the electrical wires on 5866VB between Frame 90 thru Frame 91 to

connector 5215VC

Refer to Fig. A-GBDAE Sheet 03 thru Fig. A-GBDAE Sheet 07

Reinstall the connector 5215VC

1 Receptacle Item (433) Retained at

removal

attached with:

4 Screw NAS1100-04-6 Item 430

4 Washer NAS1149CN416R Item 431

4 Nut MS21042-04 Item 432

and install:

1 Screw NAS1801-3-8 Item 314

1 Washer NAS1149C0332R Item 417

2 Clamp Item (437) Retained at

removal

1 Nut-Clip NSA5066-3-2 Item 448

or alternative install:

1 Washer NAS1149C0332R Item 417

3 Clamp Item (437) Retained at

removal

1 Nut-Clip NSA5066-3-1 Item 439

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 506

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SERVICE BULLETIN

2 Spacer Item (442) Retained at

removal

1 Screw NAS1801-3-27 Item 501

and install:

12 Clamp Item (437) Retained at

removal

2 Spacer Item (442) Retained at

removal

5 Clamp AS21919WCH13 Item 350

8 Washer NAS1149C0332R Item 417

7 Screw NAS1801-3-8 Item 314

1 Screw NAS1801-3-27 Item 501

2 Spacer NSA5527-03-02 Item 320

3 Nut NAS1291C3M Item 419

2 Screw NAS1801-3-18 Item 444

1 Nut NSA5067-3-1 Item 353

7 Route the wire, Item 401, from the 3 way transition, Item 492, to the splice

5410VS and route to the wire 5866VB with:

Refer to Fig. A-GBDAE Sheet 03 and Fig. A-GBDAE Sheet 07 thru Fig. AGBDAE Sheet 08

1 Protection SystemLightningF9249016013200 Item 451

1 Protection SystemLightning

F9249016510800 Item 489

1 Protection SystemLightningF9249016110900 Item 511

0.1 Tubing-Heat-Shrinkable E0126-06L Item 488

0.35 Tubing-Heat-Shrinkable E0126-01L Item 510

NOTE: Cut the sleeve to the necessary length.

and install:

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 507

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@A340

SERVICE BULLETIN

4 Placard Set F9237000207400 Item 402

8 Install the protection, Item 511, at Frame 93 with:

1 Nut ABS0520-07P Item 518

1 Support-Strain Relief ABS0513-09 Item 517

9 Install the electrical wire at Frame 93 on 5865VB and 5866VB with:

Refer to Fig. A-GBDAE Sheet 01 and Fig. A-GBDAE Sheet 09 thru Fig. AGBDAE Sheet 10

3 Spacer NSA5527-03-02 Item 320

1 Clamp MS21919WCH8 Item 352

1 Washer NAS1149C0332R Item 417

1 Nut NAS1291C3M Item 419

6 Clamp Item (437) Retained at

removal

5 Spacer Item (442) Retained at

removal

2 Screw NAS1801-08-8 Item 449

1 Screw NAS1801-3-15 Item 465

1 Strip ASNA0182-4ADL Item 469

3 Nut NAS1291C08M Item 470

5 Washer NAS1149CN816R Item 471

1 Strip-Bonding ASNA0182-3ADL Item 472

2 Screw NAS1801-08-36 Item 475

2 Nut-Clip NSA5066-08-1 Item 476

1 Clamp AS21919WCH07 Item 515

1 Clamp AS21919WCH14 Item 521

1 Screw NAS1801-08-12 Item 528

3 Clamp AS21919WCH02 Item 536

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 508

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@A340

SERVICE BULLETIN

1 Clamp AS21919WCH09 Item 537

for the wire connection install:

0.06 Tubing-Heat-Shrinkable E0718-01 Item 479

0.1 Tubing-Heat Shrink NSA937210MB0300 Item 480

2 Splice NSA936809RG0001 Item 481

(28) Subtask 364033-831-206-003 - Remove the sensing elements in the AFT and Bulk

cargo compartments

Work Zones and Access Panels

Zone Access/Work location

From 160 Work location Frame 55

To 310 Work location Frame 83

Manpower Resources

Manhours 5.25

Minimum number of person 1

Subtask elapsed time 5.25

Skills ELECTRICAL

References

Fig. A-GBFAE

Removal of the Sensing Elements in the

Bulk and AFT Cargo Compartments

Sheet 01

Sheet 02

Sheet 03

(a) Remove the sensing elements in the AFT and Bulk cargo compartments

1 Remove the sensing elements between Frame 55 thru Frame 83

Refer to Fig. A-GBFAE Sheet 01 thru Fig. A-GBFAE Sheet 03

Remove:

FIN 26HF

1 Sensing Element 35593-2-255 Item (564)

FIN 27HF

1 Sensing Element 35609-2-255 Item (566)

FIN 28HF

1 Sensing Element 35593-2-255 Item (358)

FIN 29HF

1 Sensing Element 35593-2-255 Item (563)

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 509

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@A340

SERVICE BULLETIN

FIN 30HF

1 Sensing Element 35609-2-255 Item (562)

FIN 31HF

1 Sensing Element 35609-2-255 Item (570)

FIN 32HF

1 Sensing Element 35609-2-255 Item (572)

attached with:

7 Nut Item (599) Retain

7 Flange Item (592) Discard

17 Sleeve Item (602) Discard

17 Clamp Item (357) Discard

10 Screw Item (408) Retain

10 Spacer Item (609) Discard

16 Clip Nut Item (399) Retain

16 Screw Item (601) Retain

2 Remove the sensing element at Frame 80/82

Refer to Fig. A-GBFAE Sheet 01 and Fig. A-GBFAE Sheet 03

Remove:

FIN 32HF

1 Sensing Element 35609-2-255 Item (572)

with:

1 Washer Item (602) Discard

1 Washer Item (604) Discard

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 510

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SERVICE BULLETIN

(29) Subtask 364033-831-212-002 - Drill an additional hole for the dual loop overheat

leak detection in the CFK pressure bulkhead

Manpower Resources

Manhours 0.75

Minimum number of person 1

Subtask elapsed time 0.75

Skills AIRFRAME

References

Fig. A-GBMAE

Hole Location and Dimensions for the

Sensing Element Installation in the CFK

Pressure Bulkhead

Sheet 01

(a) Drill the hole for the dual loop overheat leak detection in the pressure bulkhead

For dimensions refer to Fig. A-GBMAE Sheet 01

1 Drill the additional sensing element hole into the pressure bulkhead Frame

80/82 with a diameter of 13.5mm (0.53in.)

(30) Subtask 364033-831-207-003 - Install the sensing elements in the AFT and Bulk

cargo compartments

Work Zones and Access Panels

Zone Access/Work location

From 160 Work location Frame 55

To 310 Work location Frame 83

Manpower Resources

Manhours 11.25

Minimum number of person 1

Subtask elapsed time 11.25

Skills ELECTRICAL

Material necessary to do the job

Kit 364033D12R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

57 D3627006026600 1 PLACARD

355 NSA5549-00 1 CONNECTR

356 F3627011520400 1 PLACARD

357 NSA5543-00 27 CLAMP

358 35587-2-255 2 SNSGELEM

389 F3627011520000 1 PLACARD

562 35602-2-255 2 ELEMENT

563 35600-2-255 2 SNSGELEM

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 511

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SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

564 35586-2-255 2 ELEMENT

566 35594-2-255 2 SNSGELEM

570 35604-2-255 2 SNSGELEM

572 35597-2-255 1 SNSGELEM

574 35599-3-255 1 ELEMENT

591 F3627011520600 1 PLACARD

592 NSA5546-00 7 ANGLE

593 F3627011522200 1 PLACARD

594 F3627011520800 2 PLACARD

596 A2117050220000 1 RING

597 NAS1149C0832R 1 WASHER

602 NSA5539S 176 SLEEVE

604 NAS1149C0863R 1 WASHER

606 F3627011520200 2 PLACARD

607 NAS1919C04S02U 14 RIVET

609 NSA5527-03-01 1 SPACER

610 NSA5538-00 2 CLAMP

611 F3627011521000 1 PLACARD

612 NSA5542-00 6 NUT

805 NAS1802-3-13 1 SCREW

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Lockwire 0.6 Mm 19-018 As required

References

Aircraft Maintenance Manual (AMM) Task 36-22-17-400-801

Fig. A-GBGAE

Installation of the Sensing Elements in

the Bulk and AFT Cargo Compartments

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

Sheet 09

Fig. A-GBNAA

Tolerances for the Waviness and Bend

in the Electrical Wiring

Sheet 01

Sheet 02

(a) Install the sensing elements in the AFT and Bulk cargo compartments

Refer to AMM Task 36-22-17-400-801

1 For the installation of the sensing elements install the connection flanges

Refer to Fig. A-GBGAE Sheet 01 thru Fig. A-GBGAE Sheet 08

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 512

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@A340

SERVICE BULLETIN

Put the angles, Item 592, in position within the given tolerance area, transfer

drill the rivet holes to the duct-brackets with the diameter between 3.28 mm

and 3.35 mm (0.129 in and 0.132 in) and install:

7 Angle NSA5546-00 Item 592

with:

14 Rivet-Blind NAS1919C04S02U Item 607

2 Install the sensing elements between Frame 55 thru Frame 83

Refer to Fig. A-GBGAE Sheet 01 thru Fig. A-GBGAE Sheet 09

For the tolerances for waviness and bend in wires, refer to Fig. A-GBNAA

Sheet 01 thru Fig. A-GBNAA Sheet 02.

NOTE: The length compensation of the sensing elements must be

done at the couplings or retainer rings.

NOTE: The sensing elements must be installed in front of the

ventilation holes.

Install:

2 Sensing Element 35587-2-255 Item 358

2 Sensing Element 35602-2-255 Item 562

2 Sensing Element 35600-2-255 Item 563

2 Sensing Element 35586-2-255 Item 564

2 Sensing Element 35594-2-255 Item 566

2 Sensing Element 35604-2-255 Item 570

1 Sensing Element 35597-2-255 Item 572

1 Sensing Element 35599-3-255 Item 574

with:

1 Connector NSA5549-00 Item 355

27 Clamp NSA5543-00 Item 357

16 Clip Nut Item (399) Retained at

removal

6 Screw Item (408) Retained at

removal

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 513

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@A340

SERVICE BULLETIN

1 Ring-Sealing A2117050220000 Item 596

1 Washer NAS1149C0832R Item 597

16 Screw Item (601) Retained at

removal

176 Sleeve-Protective NSA5539S Item 602

1 Washer NAS1149C0863R Item 604

1 Spacer NSA5527-03-01 Item 609

2 Clamp NSA5538-00 Item 610

6 Nut NSA5542-00 Item 612

6 Nut Item (599) Retained at

removal

1 Screw NAS1802-3-13 Item 805

NOTE: Secure the nuts, Item 612/(599), with lockwire:

Lockwire 0.6 Mm 19-018 As required

3 Install the identification placards of the sensing-elements between Frame 55

thru Frame 83

Refer to Fig. A-GBGAE Sheet 01 thru Fig. A-GBGAE Sheet 09

Install:

1 Placard F3627011520400 Item 356

1 Placard F3627011520000 Item 389

1 Placard F3627011520600 Item 591

2 Placard F3627011520800 Item 594

1 Placard F3627011522200 Item 593

1 Placard F3627011521000 Item 611

2 Placard F3627011520200 Item 606

1 Placard D3627006026600 Item 57

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 514

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SERVICE BULLETIN

(31) Subtask 364033-410-003-001 - If removed, install the ducts between FR39 and

FR40.

Work Zones and Access Panels

Zone Access/Work location

190

Manpower Resources

Manhours 2.00

Minimum number of person 1

Subtask elapsed time 2.00

Skills AIRFRAME

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801

Fig. A-FBPAA

Removal/Installation of the Ducts

Between FR39 and FR40 for Access

Sheet 01

(a) Install :

Fig. A-FBPAA

(Refer to AMM Task 21-20-00-410-801)

1 Duct assy Item (125) Retained at

removal

1 Duct assy Item (126) Retained at

removal

1 Duct assy Item (127) Retained at

removal

(32) Subtask 364033-831-208-003 - Remove the sensing elements in the rear fuselage

Work Zones and Access Panels

Zone Access/Work location

310 Work location from Frame 80 to Frame 95

Manpower Resources

Manhours 2.75

Minimum number of person 1

Subtask elapsed time 2.75

Skills ELECTRICAL

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 515

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SERVICE BULLETIN

References

Fig. A-GBHAE

Removal of the Sensing Elements in the

Rear Fuselage Section

Sheet 01

Sheet 02

Sheet 03

Sheet 04

(a) Remove the sensing elements in the rear fuselage

1 Remove the sensing elements between Frame 80/82 thru Frame 95

Refer to Fig. A-GBHAE Sheet 01 thru Fig. A-GBHAE Sheet 04

Remove:

FIN 139HF

1 Sensing Element 35558-2-310 Item (362) Discard

FIN 140HF

1 Sensing Element 35636-2-310 Item (365) Discard

FIN 33HF

1 Sensing Element 35660-2-310 Item (368) Discard

FIN 34HF

1 Sensing Element 35301-75 Item (361) Discard

attached with:

3 Screw Item (601) Discard

35 Screw Item (601) Retain

45 Sleeve Item (602) Discard

2 Screw Item (620) Retain

2 Spacer Item (609) Retain

37 Clamp Item (610) Discard

3 Clamp Item (357) Retain

1 Clamp Item (621) Discard

37 Nut-Clip Item (399) Retain

3 Flange Item (592) Discard

3 Nut Item (599) Retain

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 516

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@A340

SERVICE BULLETIN

2 Remove the connector of the sensing element at Frame 80/82

Refer to Fig. A-GBHAE Sheet 01 thru Fig. A-GBHAE Sheet 04

Remove:

1 Connector Item (355) Discard

1 Washer Item (596) Discard

1 Washer Item (604) Discard

(33) Subtask 364033-831-211-001 - Remove the sensing element, FIN 149HF, previously

installed with Service Bulletin No. A340-36-4028

Manpower Resources

Manhours 4.25

Minimum number of person 1

Subtask elapsed time 4.25

Skills ELECTRICAL

Material necessary to do the job

Kit 364033D02R04

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

401 F9297000500200 1 EQUIPMNT

402 F9237000207400 1 PLCRDSET

479 E0718-01 0.06 TUBING

480 NSA937210MB0300 0.1 TUBING

481 NSA936809RG0001 2 SPLICE

References

Fig. A-GBLAE

Removal of the Sensing Element, FIN

149HF, installed with Service Bulletin

No. A340-36-4028

Sheet 01

Sheet 02

Fig. A-GWAAE

Wiring Diagram

Sheet 01

Sheet 02

Fig. A-GHAAB

Hook-up Chart

Sheet 01

(a) Remove the sensing element, FIN 149HF, previously installed with Service Bulletin

No. A340-36-4028

1 Remove the electrical splice 5865VSA and 5865VSB at Frame 83

Refer to Fig. A-GBLAE Sheet 01 thru Fig. A-GBLAE Sheet 02

Refer to Fig. A-GWAAE Sheet 01 thru Fig. A-GWAAE Sheet 02

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 517

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SERVICE BULLETIN

Refer to Fig. A-GHAAB Sheet 01, END 1, Lines 7 and 8

Remove:

2 Sleeve Item (479) Discard

2 Sleeve Item (480) Discard

2 Splice Item (481) Discard

2 Remove the sensing element, 149HF between Frame 80/82 thru Frame 83

Refer to Fig. A-GBLAE Sheet 01 thru Fig. A-GBLAE Sheet 02

Remove:

FIN 149HF

1 Sensing 35610-2-255 Item (544) Discard

and

FIN 150HF

1 Sensing wire 35301-74 Item (542) Discard

FIN 151HF

1 Sensing wire 35301-75 Item (543) Discard

attached with:

6 Clamp Item (357) Discard

13 Sleeve Item (602) Discard

1 Clamp Item (610) Discard

7 Screw Item (601) Discard

1 Screw Item (493) Discard

8 Washer Item (494) Discard

2 Nut Item (612) Discard

1 Bonding strap Item (540) Discard

1 Nut Item (419) Discard

2 Plate Item (541) Discard

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 518

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SERVICE BULLETIN

As

required

Lockwire Discard

(b) Modify the electrical wiring of the removed overheat sensing element 149HF

Between Frame 80/82 thru Frame 83 put the electrical wire in position on 5865VB

Refer to Fig. A-GBLAE Sheet 01 thru Fig. A-GBLAE Sheet 02

Refer to Fig. A-GWAAE Sheet 01 thru Fig. A-GWAAE Sheet 02

Install:

1 Equipment AssyElectricalF9297000500200 Item 401

with:

0.06 Tubing-Heat-Shrinkable E0718-01 Item 479

0.1 Tubing-Heat Shrink NSA937210MB0300 Item 480

2 Splice NSA936809RG0001 Item 481

Install the identification placard:

1 Placard Set F9237000207400 Item 402

(34) Subtask 364033-831-209-003 - Install the sensing elements in the rear fuselage

Manpower Resources

Manhours 5.75

Minimum number of person 1

Subtask elapsed time 5.75

Skills ELECTRICAL

Material necessary to do the job

Kit 364033D15R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

59 NSA5545-00 3 ANGLE

313 NAS1801-3-19 2 SCREW

314 NAS1801-3-8 5 SCREW

355 NSA5549-00 1 CONNECTR

357 NSA5543-00 38 CLAMP

359 F3627014700200 1 BRACKET

360 35301-74 1 CABLE

361 35301-75 1 CABLE

362 35563-2-255 1 ELEMENT

363 35566-2-255 1 ELEMENT

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 519

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@A340

SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

365 35616-2-255 2 ELEMENT

367 35637-3-255 1 ELEMENT

368 35640-2-255 1 SNSGELEM

372 AS21919WCH04 12 CLAMP

373 AS21919WCH10 2 CLAMP

374 F3617052620200 1 PLACARD

392 F3627011521400 1 PLACARD

393 F3627011521600 2 PLACARD

394 F3627011521800 2 PLACARD

396 NAS1149F0332P 5 WASHER

397 NSA5527-03-04 2 SPACER

416 NAS1801-3-9 5 SCREW

591 F3617052620000 1 PLACARD

596 A2117050220000 1 RING

597 NAS1149C0832R 1 WASHER

602 NSA5539S 92 SLEEVE

604 NAS1149C0863R 1 WASHER

607 NAS1919C04S02U 6 RIVET

608 D3627006026800 1 PLACARD

609 NSA5527-03-01 3 SPACER

610 NSA5538-00 2 CLAMP

612 NSA5542-00 3 NUT

640 MS21042-3 5 NUT

682 NAS1149D0332K 7 WASHER

805 NAS1802-3-13 2 SCREW

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Lockwire 0.6 Mm 19-018 As required

References

Fig. A-GBJAE

Installation of the Sensing Elements in

the Rear Fuselage Section

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

(a) Install the sensing elements in the rear fuselage

1 For the installation of the sensing elements install the connection flanges

Refer to Fig. A-GBJAE Sheet 01 thru Fig. A-GBJAE Sheet 08

Install:

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 520

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@A340

SERVICE BULLETIN

3 Connection Flanges NSA5545-00 Item 59

with:

6 Rivet-Blind NAS1919C04S02U Item 607

2 Install a bracket for the correct attachment of the sensing elements at Frame

83

Refer to Fig. A-GBJAE Sheet 01 and Fig. A-GBJAE Sheet 03

1 Bracket Assy F3627014700200 Item 359

with:

2 Screw NAS1801-3-8 Item 314

4 Washer NAS1149F0332P Item 396

2 Nut MS21042-3 Item 640

3 Install the sensing elements between Frame 80/82 thru Frame 95

Refer to Fig. A-GBJAE Sheet 01thru Fig. A-GBJAE Sheet 08

NOTE: The length compensation of the sensing elements must be

done at the couplings or retainer rings.

NOTE: The sensing elements must be installed in front of the

ventilation holes.

Install:

FIN 361HF

1 Cable-Electrical

Interconnecting

35301-74 Item 360

FIN 34HF

1 Cable-Electrical

Interconnecting

35301-75 Item 361

FIN 359HF

1 Sensing Element 35566-2-255 Item 363

FIN 360HF

1 Sensing Element 35616-2-255 Item 365

FIN 140HF

1 Sensing Element 35616-2-255 Item 365

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 521

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SERVICE BULLETIN

FIN 139HF

1 Sensing Element 35563-2-255 Item 362

FIN 358HF

1 Sensing Element 35637-3-255 Item 367

FIN 33HF

1 Sensing-Element 35640-2-255 Item 368

with:

1 Connector NSA5549-00 Item 355

1 Washer NAS1149C0832R Item 597

1 Ring-Sealing A2117050220000 Item 596

1 Washer NAS1149C0863R Item 604

attached with:

37 Nut-Clip Item (399) Retained at

removal

5 Spacer Item (609) Retained at

removal

4 Screw Item (620) Retained at

removal

3 Nut Item (599) Retained at

removal

2 Clamp Item (436) Retained at

removal

2 Screw NAS1801-3-19 Item 313

3 Screw NAS1801-3-8 Item 314

38 Clamp NSA5543-00 Item 357

12 Clamp AS21919WCH04 Item 372

2 Clamp AS21919WCH10 Item 373

1 Washer NAS1149F0332P Item 396

2 Spacer NSA5527-03-04 Item 397

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 522

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SERVICE BULLETIN

5 Screw NAS1801-3-9 Item 416

92 Sleeve-Protective NSA5539S Item 602

3 Spacer NSA5527-03-01 Item 609

2 Clamp NSA5538-00 Item 610

3 Nut NSA5542-00 Item 612

3 Nut MS21042-3 Item 640

7 Washer NAS1149D0332K Item 682

2 Screw NAS1802-3-13 Item 805

NOTE: Secure the nuts, Item 612/(612), with lockwire:

Lockwire 0.6 Mm 19-018 As required

4 Install the identification placards of the sensing-elements between Frame

80/82 thru Frame 95

Refer to Fig. A-GBJAE Sheet 01thru Fig. A-GBJAE Sheet 08

Install:

1 Placard F3617052620200 Item 374

1 Placard F3627011521400 Item 392

2 Placard F3627011521600 Item 393

2 Placard F3627011521800 Item 394

1 Placard F3617052620000 Item 591

1 Placard D3627006026800 Item 608

(35) Subtask 364033-831-210-002 - Install the sleeves at the APU Bleed Air Duct

Work Zones and Access Panels

Zone Access/Work location

310 Work location from Frame 80 to Frame 95

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills ELECTRICAL

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 523

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SERVICE BULLETIN

Material necessary to do the job

Kit 364033D17R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

377 F3617062400400 1 SLEEVE

380 F3617062401600 1 SLEEVE

382 F3617062402200 1 SLEEVE

383 F3617062403200 1 SLEEVE

384 F3617062403400 1 SLEEVE

385 F3617062403600 1 SLEEVE

386 F3617062403800 1 SLEEVE

387 F3617062404000 1 SLEEVE

602 NSA5539S 6 SLEEVE

References

Fig. A-GBKAC

Installation of the Sleeves at the APU

Bleed Air Duct

Sheet 01

(a) Install the sleeves at the APU Bleed Air Duct between Frame 80/82 thru Frame 95

Refer to Fig. A-GBKAC Sheet 01

install the sleeves and close them with the adhesive strips:

1 Sleeve Assy F3617062400400 Item 377

1 Sleeve Assy F3617062401600 Item 380

1 Sleeve Assy F3617062402200 Item 382

1 Sleeve F3617062403200 Item 383

1 Sleeve F3617062403400 Item 384

1 Sleeve F3617062403600 Item 385

1 Sleeve F3617062403800 Item 386

1 Sleeve F3617062404000 Item 387

Close the sleeves with:

6 Sleeve-Protective NSA5539S Item 602

NOTE: Make sure that the blowout apertures of the blankets are close to

(under) the sensing elements.

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 524

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SERVICE BULLETIN

**CONF ALL

D. TEST

**CONF 001

(1) Subtask 364033-861-001-001 - Energize Electrical Network

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 24-41-00-861-801

(a) In the cockpit, on the panel 235VU, push these pushbutton switches :

- BAT 1, BAT 2, APU BAT,

- GEN 1, (2, 3, 4), APU GEN,

- EXT A (B).

(b) Remove the warning notices.

(c) Energize the aircraft electrical circuits (Refer to AMM Task 24-41-00-861-801).

(d) Remove the safety clips and tags and close the following circuit breakers :

PANEL DESIGNATION FIN LOCATION SEE

NOTES

742VU 701PP 10PB1 72 S

742VU 702PP 10PB2 71 S

(2) Subtask 364033-700-201-001 - Test

Manpower Resources

Skills ELECTRICAL

References

Aircraft Maintenance Manual (AMM) 36-22-17, Page Block 401

(a) Do the test after removal/installation of the Auxiliary Power Unit (APU) Bleed-air

Duct Sensing Elements (Refer to AMM 36-22-17, Page Block 401).

(3) Subtask 364033-700-001-001 - Testing

Manpower Resources

Skills NON SPECIFIC

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 525

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SERVICE BULLETIN

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801

Task 21-26-00-710-803

Task 22-96-00-740-801

Task 22-97-00-740-801

Task 25-21-41-400-801

Task 25-75-41-400-801

Task 31-50-00-710-803

Task 31-50-00-740-801

Task 31-60-00-710-802

Task 33-13-00-710-801

Task 33-14-00-710-801

Task 36-11-34-400-802

Task 36-12-00-710-801

Task 36-12-41-400-801

Task 36-22-00-710-806

Elec. Std. Practices Manual (ESPM) 20-52-10

(a) Preliminary Tests :

NOTE: If the aircraft is operated in actual CAT III conditions, you must

also do the LAND CAT III capability test (Refer to AMM Task

22-97-00-740-801).

1 On each connector which was disconnected :

- Do the checks as defined by ESPM 20-52-10.

NOTE: The Functional test and/or operational test requested by this

ESPM procedure is given hereafter.

2 Do the Operational Test of the Instrument and Panel Integral Lighting (Refer to

AMM Task 33-13-00-710-801).

3 Do the Operational Test of Lights (Refer to AMM Task 33-14-00-710-801).

4 Do the Operational Test of the Avionics-Equipment Ventilation System (Refer

to AMM Task 21-26-00-710-803).

5 Do the Bite Test of the Auto Flight System (SYSTEM TEST) (Refer to AMM

Task 22-96-00-740-801).

6 Do the Operational Test of the Electronic Centralized Aircraft Monitoring

(ECAM) Control Panel (Refer to AMM Task 31-50-00-710-803).

7 Do the test of the Flight Warning System (FWS) (Refer to AMM Task

31-50-00-740-801).

8 Do the Operational Test of the Electronic Instrument System (EIS) (Refer to

AMM Task 31-60-00-710-802).

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 526

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SERVICE BULLETIN

(b) Test of the equipments :

1 Do the test procedure as specified after the installation of the passenger seats

(Refer to AMM Task 25-21-41-400-801).

2 If applicable, do the test procedure as specified after the installation

of the Lower-Deck Mobile Crew-Rest (LD-MCR) (Refer to AMM Task

25-75-41-400-801).

3 If ducts removed, do the test procedure as specified after the installation of the

APU bleed air ducts (Refer to AMM Task 36-12-41-400-801).

4 If ducts removed, do the test procedure as specified after the installation of the

air conditioning distribution ducts (Refer to AMM Task 21-20-00-410-801).

5 Do the test procedure as specified in the installation of the BMC (FIN 1HA1,

1HA2, 1HA3 and 1HA4) (Refer to AMM Task 36-11-34-400-802).

(c) Test of the connectors :

1 Test of the connectors 2712VC, 3506VC, 3672VC and 3520VC :

a Do the Operational Test of the overheat detection system (Refer to AMM

Task 36-22-00-710-806).

2 Test of the connector 2615VC and of the Terminal Block 2901VT :

a Do the Operational Test of the APU bleed-air supply and crossbleed

system (Refer to AMM Task 36-12-00-710-801).

**CONF 002

(1) Subtask 364033-861-001-001 - Energize Electrical Network

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 24-41-00-861-801

(a) In the cockpit, on the panel 235VU, push these pushbutton switches :

- BAT 1, BAT 2, APU BAT,

- GEN 1, (2, 3, 4), APU GEN,

- EXT A (B).

(b) Remove the warning notices.

(c) Energize the aircraft electrical circuits (Refer to AMM Task 24-41-00-861-801).

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 527

6

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SERVICE BULLETIN

(d) Remove the safety clips and tags and close the following circuit breakers :

PANEL DESIGNATION FIN LOCATION SEE

NOTES

742VU 701PP 10PB1 72 S

742VU 702PP 10PB2 71 S

(2) Subtask 364033-700-201-001 - Test

Manpower Resources

Skills ELECTRICAL

References

Aircraft Maintenance Manual (AMM) 36-22-17, Page Block 401

(a) Do the test after removal/installation of the Auxiliary Power Unit (APU) Bleed-air

Duct Sensing Elements (Refer to AMM 36-22-17, Page Block 401).

(3) Subtask 364033-700-001-001 - Testing

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801

Task 21-26-00-710-803

Task 22-96-00-740-801

Task 22-97-00-740-801

Task 25-21-41-400-801

Task 25-75-41-400-801

Task 31-50-00-710-803

Task 31-50-00-740-801

Task 31-60-00-710-802

Task 33-13-00-710-801

Task 33-14-00-710-801

Task 36-11-34-400-802

Task 36-12-00-710-801

Task 36-12-41-400-801

Task 36-22-00-710-806

Elec. Std. Practices Manual (ESPM) 20-52-10

(a) Preliminary Tests :

NOTE: If the aircraft is operated in actual CAT III conditions, you must

also do the LAND CAT III capability test (Refer to AMM Task

22-97-00-740-801).

1 On each connector which was disconnected :

- Do the checks as defined by ESPM 20-52-10.

NOTE: The Functional test and/or operational test requested by this

ESPM procedure is given hereafter.

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 528

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SERVICE BULLETIN

2 Do the Operational Test of the Instrument and Panel Integral Lighting (Refer to

AMM Task 33-13-00-710-801).

3 Do the Operational Test of Lights (Refer to AMM Task 33-14-00-710-801).

4 Do the Operational Test of the Avionics-Equipment Ventilation System (Refer

to AMM Task 21-26-00-710-803).

5 Do the Bite Test of the Auto Flight System (SYSTEM TEST) (Refer to AMM

Task 22-96-00-740-801).

6 Do the Operational Test of the Electronic Centralized Aircraft Monitoring

(ECAM) Control Panel (Refer to AMM Task 31-50-00-710-803).

7 Do the test of the Flight Warning System (FWS) (Refer to AMM Task

31-50-00-740-801).

8 Do the Operational Test of the Electronic Instrument System (EIS) (Refer to

AMM Task 31-60-00-710-802).

(b) Test of the equipments :

1 Do the test procedure as specified after the installation of the passenger seats

(Refer to AMM Task 25-21-41-400-801).

2 If applicable, do the test procedure as specified after the installation

of the Lower-Deck Mobile Crew-Rest (LD-MCR) (Refer to AMM Task

25-75-41-400-801).

3 If ducts removed, do the test procedure as specified after the installation of the

APU bleed air ducts (Refer to AMM Task 36-12-41-400-801).

4 If ducts removed, do the test procedure as specified after the installation of the

air conditioning distribution ducts (Refer to AMM Task 21-20-00-410-801).

5 Do the test procedure as specified in the installation of the BMC (FIN 1HA1,

1HA2, 1HA3 and 1HA4) (Refer to AMM Task 36-11-34-400-802).

(c) Test of the connectors :

1 Test of the connectors 2712VC, 3506VC, 3672VC and 3520VC :

a Do the Operational Test of the overheat detection system (Refer to AMM

Task 36-22-00-710-806).

2 Test of the connector 2615VC and of the Terminal Block 2901VT :

a Do the Operational Test of the APU bleed-air supply and crossbleed

system (Refer to AMM Task 36-12-00-710-801).

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 529

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SERVICE BULLETIN

**CONF 003

(1) Subtask 364033-861-001-001 - Energize Electrical Network

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 24-41-00-861-801

(a) In the cockpit, on the panel 235VU, push these pushbutton switches :

- BAT 1, BAT 2, APU BAT,

- GEN 1, (2, 3, 4), APU GEN,

- EXT A (B).

(b) Remove the warning notices.

(c) Energize the aircraft electrical circuits (Refer to AMM Task 24-41-00-861-801).

(d) Remove the safety clips and tags and close the following circuit breakers :

PANEL DESIGNATION FIN LOCATION SEE

NOTES

742VU 701PP 10PB1 72 S

742VU 702PP 10PB2 71 S

(2) Subtask 364033-700-201-001 - Test

Manpower Resources

Skills ELECTRICAL

References

Aircraft Maintenance Manual (AMM) 36-22-17, Page Block 401

(a) Do the test after removal/installation of the Auxiliary Power Unit (APU) Bleed-air

Duct Sensing Elements (Refer to AMM 36-22-17, Page Block 401).

(3) Subtask 364033-700-001-001 - Testing

Manpower Resources

Skills NON SPECIFIC

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 530

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SERVICE BULLETIN

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801

Task 21-26-00-710-803

Task 22-96-00-740-801

Task 22-97-00-740-801

Task 25-21-41-400-801

Task 25-75-41-400-801

Task 31-50-00-710-803

Task 31-50-00-740-801

Task 31-60-00-710-802

Task 33-13-00-710-801

Task 33-14-00-710-801

Task 36-11-34-400-802

Task 36-12-00-710-801

Task 36-12-41-400-801

Task 36-22-00-710-806

Elec. Std. Practices Manual (ESPM) 20-52-10

(a) Preliminary Tests :

NOTE: If the aircraft is operated in actual CAT III conditions, you must

also do the LAND CAT III capability test (Refer to AMM Task

22-97-00-740-801).

1 On each connector which was disconnected :

- Do the checks as defined by ESPM 20-52-10.

NOTE: The Functional test and/or operational test requested by this

ESPM procedure is given hereafter.

2 Do the Operational Test of the Instrument and Panel Integral Lighting (Refer to

AMM Task 33-13-00-710-801).

3 Do the Operational Test of Lights (Refer to AMM Task 33-14-00-710-801).

4 Do the Operational Test of the Avionics-Equipment Ventilation System (Refer

to AMM Task 21-26-00-710-803).

5 Do the Bite Test of the Auto Flight System (SYSTEM TEST) (Refer to AMM

Task 22-96-00-740-801).

6 Do the Operational Test of the Electronic Centralized Aircraft Monitoring

(ECAM) Control Panel (Refer to AMM Task 31-50-00-710-803).

7 Do the test of the Flight Warning System (FWS) (Refer to AMM Task

31-50-00-740-801).

8 Do the Operational Test of the Electronic Instrument System (EIS) (Refer to

AMM Task 31-60-00-710-802).

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 531

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@A340

SERVICE BULLETIN

(b) Test of the equipments :

1 Do the test procedure as specified after the installation of the passenger seats

(Refer to AMM Task 25-21-41-400-801).

2 If applicable, do the test procedure as specified after the installation

of the Lower-Deck Mobile Crew-Rest (LD-MCR) (Refer to AMM Task

25-75-41-400-801).

3 If ducts removed, do the test procedure as specified after the installation of the

APU bleed air ducts (Refer to AMM Task 36-12-41-400-801).

4 If ducts removed, do the test procedure as specified after the installation of the

air conditioning distribution ducts (Refer to AMM Task 21-20-00-410-801).

5 Do the test procedure as specified in the installation of the BMC (FIN 1HA1,

1HA2, 1HA3 and 1HA4) (Refer to AMM Task 36-11-34-400-802).

(c) Test of the connectors :

1 Test of the connectors 2712VC, 3506VC, 3672VC and 3520VC :

a Do the Operational Test of the overheat detection system (Refer to AMM

Task 36-22-00-710-806).

2 Test of the connector 2615VC and of the Terminal Block 2901VT :

a Do the Operational Test of the APU bleed-air supply and crossbleed

system (Refer to AMM Task 36-12-00-710-801).

**CONF 004

(1) Subtask 364033-861-001-001 - Energize Electrical Network

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 24-41-00-861-801

(a) In the cockpit, on the panel 235VU, push these pushbutton switches :

- BAT 1, BAT 2, APU BAT,

- GEN 1, (2, 3, 4), APU GEN,

- EXT A (B).

(b) Remove the warning notices.

(c) Energize the aircraft electrical circuits (Refer to AMM Task 24-41-00-861-801).

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 532

6

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SERVICE BULLETIN

(d) Remove the safety clips and tags and close the following circuit breakers :

PANEL DESIGNATION FIN LOCATION SEE

NOTES

742VU 701PP 10PB1 72 S

742VU 702PP 10PB2 71 S

(2) Subtask 364033-700-201-001 - Test

Manpower Resources

Skills ELECTRICAL

References

Aircraft Maintenance Manual (AMM) 36-22-17, Page Block 401

(a) Do the test after removal/installation of the Auxiliary Power Unit (APU) Bleed-air

Duct Sensing Elements (Refer to AMM 36-22-17, Page Block 401).

(3) Subtask 364033-700-001-001 - Testing

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801

Task 21-26-00-710-803

Task 22-96-00-740-801

Task 22-97-00-740-801

Task 25-21-41-400-801

Task 25-75-41-400-801

Task 31-50-00-710-803

Task 31-50-00-740-801

Task 31-60-00-710-802

Task 33-13-00-710-801

Task 33-14-00-710-801

Task 36-11-34-400-802

Task 36-12-00-710-801

Task 36-12-41-400-801

Task 36-22-00-710-806

Elec. Std. Practices Manual (ESPM) 20-52-10

(a) Preliminary Tests :

NOTE: If the aircraft is operated in actual CAT III conditions, you must

also do the LAND CAT III capability test (Refer to AMM Task

22-97-00-740-801).

1 On each connector which was disconnected :

- Do the checks as defined by ESPM 20-52-10.

NOTE: The Functional test and/or operational test requested by this

ESPM procedure is given hereafter.

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 533

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@A340

SERVICE BULLETIN

2 Do the Operational Test of the Instrument and Panel Integral Lighting (Refer to

AMM Task 33-13-00-710-801).

3 Do the Operational Test of Lights (Refer to AMM Task 33-14-00-710-801).

4 Do the Operational Test of the Avionics-Equipment Ventilation System (Refer

to AMM Task 21-26-00-710-803).

5 Do the Bite Test of the Auto Flight System (SYSTEM TEST) (Refer to AMM

Task 22-96-00-740-801).

6 Do the Operational Test of the Electronic Centralized Aircraft Monitoring

(ECAM) Control Panel (Refer to AMM Task 31-50-00-710-803).

7 Do the test of the Flight Warning System (FWS) (Refer to AMM Task

31-50-00-740-801).

8 Do the Operational Test of the Electronic Instrument System (EIS) (Refer to

AMM Task 31-60-00-710-802).

(b) Test of the equipments :

1 Do the test procedure as specified after the installation of the passenger seats

(Refer to AMM Task 25-21-41-400-801).

2 If applicable, do the test procedure as specified after the installation

of the Lower-Deck Mobile Crew-Rest (LD-MCR) (Refer to AMM Task

25-75-41-400-801).

3 If ducts removed, do the test procedure as specified after the installation of the

APU bleed air ducts (Refer to AMM Task 36-12-41-400-801).

4 If ducts removed, do the test procedure as specified after the installation of the

air conditioning distribution ducts (Refer to AMM Task 21-20-00-410-801).

5 Do the test procedure as specified in the installation of the BMC (FIN 1HA1,

1HA2, 1HA3 and 1HA4) (Refer to AMM Task 36-11-34-400-802).

(c) Test of the connectors :

1 Test of the connectors 2712VC, 3506VC, 3672VC and 3520VC :

a Do the Operational Test of the overheat detection system (Refer to AMM

Task 36-22-00-710-806).

2 Test of the connector 2615VC and of the Terminal Block 2901VT :

a Do the Operational Test of the APU bleed-air supply and crossbleed

system (Refer to AMM Task 36-12-00-710-801).

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 534

6

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@A340

SERVICE BULLETIN

**CONF 005

(1) Subtask 364033-861-001-001 - Energize Electrical Network

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 24-41-00-861-801

(a) In the cockpit, on the panel 235VU, push these pushbutton switches :

- BAT 1, BAT 2, APU BAT,

- GEN 1, (2, 3, 4), APU GEN,

- EXT A (B).

(b) Remove the warning notices.

(c) Energize the aircraft electrical circuits (Refer to AMM Task 24-41-00-861-801).

(d) Remove the safety clips and tags and close the following circuit breakers :

PANEL DESIGNATION FIN LOCATION SEE

NOTES

742VU 701PP 10PB1 72 S

742VU 702PP 10PB2 71 S

(2) Subtask 364033-700-201-001 - Test

Manpower Resources

Skills ELECTRICAL

References

Aircraft Maintenance Manual (AMM) 36-22-17, Page Block 401

(a) Do the test after removal/installation of the Auxiliary Power Unit (APU) Bleed-air

Duct Sensing Elements (Refer to AMM 36-22-17, Page Block 401).

(3) Subtask 364033-700-001-001 - Testing

Manpower Resources

Skills NON SPECIFIC

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 535

6

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SERVICE BULLETIN

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801

Task 21-26-00-710-803

Task 22-96-00-740-801

Task 22-97-00-740-801

Task 25-21-41-400-801

Task 25-75-41-400-801

Task 31-50-00-710-803

Task 31-50-00-740-801

Task 31-60-00-710-802

Task 33-13-00-710-801

Task 33-14-00-710-801

Task 36-11-34-400-802

Task 36-12-00-710-801

Task 36-12-41-400-801

Task 36-22-00-710-806

Elec. Std. Practices Manual (ESPM) 20-52-10

(a) Preliminary Tests :

NOTE: If the aircraft is operated in actual CAT III conditions, you must

also do the LAND CAT III capability test (Refer to AMM Task

22-97-00-740-801).

1 On each connector which was disconnected :

- Do the checks as defined by ESPM 20-52-10.

NOTE: The Functional test and/or operational test requested by this

ESPM procedure is given hereafter.

2 Do the Operational Test of the Instrument and Panel Integral Lighting (Refer to

AMM Task 33-13-00-710-801).

3 Do the Operational Test of Lights (Refer to AMM Task 33-14-00-710-801).

4 Do the Operational Test of the Avionics-Equipment Ventilation System (Refer

to AMM Task 21-26-00-710-803).

5 Do the Bite Test of the Auto Flight System (SYSTEM TEST) (Refer to AMM

Task 22-96-00-740-801).

6 Do the Operational Test of the Electronic Centralized Aircraft Monitoring

(ECAM) Control Panel (Refer to AMM Task 31-50-00-710-803).

7 Do the test of the Flight Warning System (FWS) (Refer to AMM Task

31-50-00-740-801).

8 Do the Operational Test of the Electronic Instrument System (EIS) (Refer to

AMM Task 31-60-00-710-802).

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 536

6

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@A340

SERVICE BULLETIN

(b) Test of the equipments :

1 Do the test procedure as specified after the installation of the passenger seats

(Refer to AMM Task 25-21-41-400-801).

2 If applicable, do the test procedure as specified after the installation

of the Lower-Deck Mobile Crew-Rest (LD-MCR) (Refer to AMM Task

25-75-41-400-801).

3 If ducts removed, do the test procedure as specified after the installation of the

APU bleed air ducts (Refer to AMM Task 36-12-41-400-801).

4 If ducts removed, do the test procedure as specified after the installation of the

air conditioning distribution ducts (Refer to AMM Task 21-20-00-410-801).

5 Do the test procedure as specified in the installation of the BMC (FIN 1HA1,

1HA2, 1HA3 and 1HA4) (Refer to AMM Task 36-11-34-400-802).

(c) Test of the connectors :

1 Test of the connectors 2712VC, 3506VC, 3672VC and 3520VC :

a Do the Operational Test of the overheat detection system (Refer to AMM

Task 36-22-00-710-806).

2 Test of the connector 2615VC and of the Terminal Block 2901VT :

a Do the Operational Test of the APU bleed-air supply and crossbleed

system (Refer to AMM Task 36-12-00-710-801).

**CONF ALL

E. CLOSE-UP

**CONF 001

(1) Subtask 364033-942-201-001 - Close-up

Work Zones and Access Panels

Zone Access/Work location

130 Access Door 821, Door 831

Work location from Frame 20 to Frame 39.1

Panel 132TC

Panel 132CC

Panel 132GC

Panel 132MC

Panel 132RC

Panel 132PC

Panel 132KC

160 Access Door 313AL

Work location Panel 161BC

Panel 161EC

150 Access Door 822

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 537

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@A340

SERVICE BULLETIN

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 25-52-00, Page Block 201

25-54-00, Page Block 201

52-30-00, Page Block 001

(a) In the FWD cargo compartment install the removed ceiling panels (Refer to AMM

25-52-00, Page Block 201).

(b) In the BULK cargo compartment install the removed ceiling panels (Refer to AMM

25-54-00, Page Block 201).

(c) Close the Bulk cargo compartment door (Refer to AMM 52-30-00, Page Block 001).

(2) Subtask 364033-410-004-001 - Install/Close Items Removed/Opened for access

Manpower Resources

Skills NON SPECIFIC

References

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

Task 25-21-41-400-801

Task 25-28-41-400-801

Task 25-52-00-400-801

Task 25-53-00-400-801

Task 25-75-41-400-801

Task 53-00-00-400-801

Task 53-00-00-400-802

Task 53-35-11-400-801

Task 53-35-13-400-801

Task 53-35-13-400-802

(a) Between Frame 37.4 and Frame 39.1 in the FWD cargo-compartment, install the

floor panel 132DG (Refer to AMM 06-41-53, Page Block 001 and AMM Task

53-00-00-400-802).

(b) On the RH side, between Frame 38 and Frame 39.1 in the FWD cargocompartment, install (if removed) the sidewall panels 132AX and 132ZW (Refer to

AMM 06-41-53, Page Block 001 and AMM Task 25-52-00-400-801).

(c) On the RH side, between Frame 37.1 and Frame 39.1 in the FWD cargocompartment, install (if removed) the ceiling panels 132TC and 132VC (Refer to

AMM 06-41-53, Page Block 001 and AMM Task 25-52-00-400-801).

(d) At Frame 39.2 in the FWD cargo-compartment, install (if removed) the partition

panels 132DX and 132CX (Refer to AMM 06-41-53, Page Block 001 and AMM

Task 25-52-00-400-801).

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 538

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@A340

SERVICE BULLETIN

(e) At Frame 20 in the FWD cargo-compartment, install the partition panels

131AW and 132CW (Refer to AMM 06-41-53, Page Block 001 and AMM Task

25-52-00-400-801).

(f) On the RH side, between Frame 47 and Frame 53 in the PAX compartment, install

(if removed) the Seats (Refer to AMM Task 25-21-41-400-801).

(g) On the RH side, between Frame 47 and Frame 53 in the PAX compartment, install

(if removed) the Textile Floor Covering (Refer to AMM Task 25-28-41-400-801).

(h) On the RH side, between Frame 47 and Frame 53 in the PAX compartment, install

(if removed) the floor panel 252LG (Refer to AMM Task 53-00-00-400-801).

(i) On the LH side, between Frame 53.2 and Frame 57.1 in the AFT cargo

compartment, install (if removed) the sidewall panels 151EW, 151GW and 151JW

(Refer to AMM 06-41-53, Page Block 001 and AMM Task 25-53-00-400-801).

(j) On the RH side, between Frame 53.2 and Frame 58 in the AFT cargocompartment, install (if removed) the ceiling panels 152BC, 152DC, 152FC

and 152HC (Refer to AMM 06-41-53, Page Block 001 and AMM Task

25-53-00-400-801).

(k) At Frame 53.2 in the AFT cargo-compartment, install the partition panel152CW

(Refer to AMM 06-41-53, Page Block 001 and AMM Task 25-53-00-400-801).

(l) On the LH side of the belly fairing, install (if removed) the panels 191HB,

191FB, 191KB, 193AB, 195CB, 195DB, 197AT, 197BB and 197EB (Refer to

AMM Task 53-35-11-400-801 and AMM Task 53-35-13-400-801 and AMM Task

53-35-13-400-802)

(m) On the RH side of the belly fairing, install the panels 192BZ, 192CZ, 192HB and

192GB (Refer to AMM Task 53-35-11-400-801 and AMM Task 53-35-13-400-802).

(n) If existing, remove the Lower Deck Mobile Crew Rest (LD-MCR) (Refer to AMM

Task 25-75-41-400-801).

(3) Subtask 364033-942-001-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-41-52, Page Block 001

06-41-53, Page Block 001

Task 32-12-00-410-801

Task 36-11-34-400-802

Task 36-22-17-400-801

Task 36-22-17-400-802

Task 52-10-00-410-801

52-30-00, Page Block 201

52-52-00, Page Block 001

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 539

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@A340

SERVICE BULLETIN

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

equipment.

(b) Close the FWD cargo-compartment door 821 and AFT cargo-compartment door

822 (Refer to AMM 06-41-52, Page Block 001 and AMM 52-30-00, Page Block

201).

(c) Close the door 132AZ (Refer to AMM 06-41-53, Page Block 001 and AMM

52-52-00, Page Block 001).

(d) Close the Main Landing Gear (MLG) doors (Refer to AMM Task 32-12-00-410-801).

(e) Do the close-up procedure as specified in the installation of the sensing elements

(Refer to AMM Task 36-22-17-400-801 and AMM Task 36-22-17-400-802).

(f) Do the close-up procedure as specified in the installation of the BMC (FIN 1HA1,

1HA2, 1HA3 and 1HA4) (Refer to AMM Task 36-11-34-400-802).

(g) Close the passenger/crew door(s) (Refer to AMM Task 52-10-00-410-801).

(h) Remove the access platform(s).

(i) Restore the systems and the aircraft to normal operating conditions.

**CONF 002

(1) Subtask 364033-942-201-001 - Close-up

Work Zones and Access Panels

Zone Access/Work location

130 Access Door 821, Door 831

Work location from Frame 20 to Frame 39.1

Panel 132TC

Panel 132CC

Panel 132GC

Panel 132MC

Panel 132RC

Panel 132PC

Panel 132KC

160 Access Door 313AL

Work location Panel 161BC

Panel 161EC

150 Access Door 822

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 25-52-00, Page Block 201

25-54-00, Page Block 201

52-30-00, Page Block 001

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 540

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@A340

SERVICE BULLETIN

(a) In the FWD cargo compartment install the removed ceiling panels (Refer to AMM

25-52-00, Page Block 201).

(b) In the BULK cargo compartment install the removed ceiling panels (Refer to AMM

25-54-00, Page Block 201).

(c) Close the Bulk cargo compartment door (Refer to AMM 52-30-00, Page Block 001).

(2) Subtask 364033-410-004-001 - Install/Close Items Removed/Opened for access

Manpower Resources

Skills NON SPECIFIC

References

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

Task 25-21-41-400-801

Task 25-28-41-400-801

Task 25-52-00-400-801

Task 25-53-00-400-801

Task 25-75-41-400-801

Task 53-00-00-400-801

Task 53-00-00-400-802

Task 53-35-11-400-801

Task 53-35-13-400-801

Task 53-35-13-400-802

(a) Between Frame 37.4 and Frame 39.1 in the FWD cargo-compartment, install the

floor panel 132DG (Refer to AMM 06-41-53, Page Block 001 and AMM Task

53-00-00-400-802).

(b) On the RH side, between Frame 38 and Frame 39.1 in the FWD cargocompartment, install (if removed) the sidewall panels 132AX and 132ZW (Refer to

AMM 06-41-53, Page Block 001 and AMM Task 25-52-00-400-801).

(c) On the RH side, between Frame 37.1 and Frame 39.1 in the FWD cargocompartment, install (if removed) the ceiling panels 132TC and 132VC (Refer to

AMM 06-41-53, Page Block 001 and AMM Task 25-52-00-400-801).

(d) At Frame 39.2 in the FWD cargo-compartment, install (if removed) the partition

panels 132DX and 132CX (Refer to AMM 06-41-53, Page Block 001 and AMM

Task 25-52-00-400-801).

(e) At Frame 20 in the FWD cargo-compartment, install the partition panels

131AW and 132CW (Refer to AMM 06-41-53, Page Block 001 and AMM Task

25-52-00-400-801).

(f) On the RH side, between Frame 47 and Frame 53 in the PAX compartment, install

(if removed) the Seats (Refer to AMM Task 25-21-41-400-801).

(g) On the RH side, between Frame 47 and Frame 53 in the PAX compartment, install

(if removed) the Textile Floor Covering (Refer to AMM Task 25-28-41-400-801).

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 541

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@A340

SERVICE BULLETIN

(h) On the RH side, between Frame 47 and Frame 53 in the PAX compartment, install

(if removed) the floor panel 252LG (Refer to AMM Task 53-00-00-400-801).

(i) On the LH side, between Frame 53.2 and Frame 57.1 in the AFT cargo

compartment, install (if removed) the sidewall panels 151EW, 151GW and 151JW

(Refer to AMM 06-41-53, Page Block 001 and AMM Task 25-53-00-400-801).

(j) On the RH side, between Frame 53.2 and Frame 58 in the AFT cargocompartment, install (if removed) the ceiling panels 152BC, 152DC, 152FC

and 152HC (Refer to AMM 06-41-53, Page Block 001 and AMM Task

25-53-00-400-801).

(k) At Frame 53.2 in the AFT cargo-compartment, install the partition panel152CW

(Refer to AMM 06-41-53, Page Block 001 and AMM Task 25-53-00-400-801).

(l) On the LH side of the belly fairing, install (if removed) the panels 191HB,

191FB, 191KB, 193AB, 195CB, 195DB, 197AT, 197BB and 197EB (Refer to

AMM Task 53-35-11-400-801 and AMM Task 53-35-13-400-801 and AMM Task

53-35-13-400-802)

(m) On the RH side of the belly fairing, install the panels 192BZ, 192CZ, 192HB and

192GB (Refer to AMM Task 53-35-11-400-801 and AMM Task 53-35-13-400-802).

(n) If existing, remove the Lower Deck Mobile Crew Rest (LD-MCR) (Refer to AMM

Task 25-75-41-400-801).

(3) Subtask 364033-942-001-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-41-52, Page Block 001

06-41-53, Page Block 001

Task 32-12-00-410-801

Task 36-11-34-400-802

Task 36-22-17-400-801

Task 36-22-17-400-802

Task 52-10-00-410-801

52-30-00, Page Block 201

52-52-00, Page Block 001

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

equipment.

(b) Close the FWD cargo-compartment door 821 and AFT cargo-compartment door

822 (Refer to AMM 06-41-52, Page Block 001 and AMM 52-30-00, Page Block

201).

(c) Close the door 132AZ (Refer to AMM 06-41-53, Page Block 001 and AMM

52-52-00, Page Block 001).

(d) Close the Main Landing Gear (MLG) doors (Refer to AMM Task 32-12-00-410-801).

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 542

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@A340

SERVICE BULLETIN

(e) Do the close-up procedure as specified in the installation of the sensing elements

(Refer to AMM Task 36-22-17-400-801 and AMM Task 36-22-17-400-802).

(f) Do the close-up procedure as specified in the installation of the BMC (FIN 1HA1,

1HA2, 1HA3 and 1HA4) (Refer to AMM Task 36-11-34-400-802).

(g) Close the passenger/crew door(s) (Refer to AMM Task 52-10-00-410-801).

(h) Remove the access platform(s).

(i) Restore the systems and the aircraft to normal operating conditions.

**CONF 003

(1) Subtask 364033-942-201-001 - Close-up

Work Zones and Access Panels

Zone Access/Work location

130 Access Door 821, Door 831

Work location from Frame 20 to Frame 39.1

Panel 132TC

Panel 132CC

Panel 132GC

Panel 132MC

Panel 132RC

Panel 132PC

Panel 132KC

160 Access Door 313AL

Work location Panel 161BC

Panel 161EC

150 Access Door 822

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 25-52-00, Page Block 201

25-54-00, Page Block 201

52-30-00, Page Block 001

(a) In the FWD cargo compartment install the removed ceiling panels (Refer to AMM

25-52-00, Page Block 201).

(b) In the BULK cargo compartment install the removed ceiling panels (Refer to AMM

25-54-00, Page Block 201).

(c) Close the Bulk cargo compartment door (Refer to AMM 52-30-00, Page Block 001).

(2) Subtask 364033-410-004-001 - Install/Close Items Removed/Opened for access

Manpower Resources

Skills NON SPECIFIC

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 543

6

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@A340

SERVICE BULLETIN

References

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

Task 25-21-41-400-801

Task 25-28-41-400-801

Task 25-52-00-400-801

Task 25-53-00-400-801

Task 25-75-41-400-801

Task 53-00-00-400-801

Task 53-00-00-400-802

Task 53-35-11-400-801

Task 53-35-13-400-801

Task 53-35-13-400-802

(a) Between Frame 37.4 and Frame 39.1 in the FWD cargo-compartment, install the

floor panel 132DG (Refer to AMM 06-41-53, Page Block 001 and AMM Task

53-00-00-400-802).

(b) On the RH side, between Frame 38 and Frame 39.1 in the FWD cargocompartment, install (if removed) the sidewall panels 132AX and 132ZW (Refer to

AMM 06-41-53, Page Block 001 and AMM Task 25-52-00-400-801).

(c) On the RH side, between Frame 37.1 and Frame 39.1 in the FWD cargocompartment, install (if removed) the ceiling panels 132TC and 132VC (Refer to

AMM 06-41-53, Page Block 001 and AMM Task 25-52-00-400-801).

(d) At Frame 39.2 in the FWD cargo-compartment, install (if removed) the partition

panels 132DX and 132CX (Refer to AMM 06-41-53, Page Block 001 and AMM

Task 25-52-00-400-801).

(e) At Frame 20 in the FWD cargo-compartment, install the partition panels

131AW and 132CW (Refer to AMM 06-41-53, Page Block 001 and AMM Task

25-52-00-400-801).

(f) On the RH side, between Frame 47 and Frame 53 in the PAX compartment, install

(if removed) the Seats (Refer to AMM Task 25-21-41-400-801).

(g) On the RH side, between Frame 47 and Frame 53 in the PAX compartment, install

(if removed) the Textile Floor Covering (Refer to AMM Task 25-28-41-400-801).

(h) On the RH side, between Frame 47 and Frame 53 in the PAX compartment, install

(if removed) the floor panel 252LG (Refer to AMM Task 53-00-00-400-801).

(i) On the LH side, between Frame 53.2 and Frame 57.1 in the AFT cargo

compartment, install (if removed) the sidewall panels 151EW, 151GW and 151JW

(Refer to AMM 06-41-53, Page Block 001 and AMM Task 25-53-00-400-801).

(j) On the RH side, between Frame 53.2 and Frame 58 in the AFT cargocompartment, install (if removed) the ceiling panels 152BC, 152DC, 152FC

and 152HC (Refer to AMM 06-41-53, Page Block 001 and AMM Task

25-53-00-400-801).

(k) At Frame 53.2 in the AFT cargo-compartment, install the partition panel152CW

(Refer to AMM 06-41-53, Page Block 001 and AMM Task 25-53-00-400-801).

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 544

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@A340

SERVICE BULLETIN

(l) On the LH side of the belly fairing, install (if removed) the panels 191HB,

191FB, 191KB, 193AB, 195CB, 195DB, 197AT, 197BB and 197EB (Refer to

AMM Task 53-35-11-400-801 and AMM Task 53-35-13-400-801 and AMM Task

53-35-13-400-802)

(m) On the RH side of the belly fairing, install the panels 192BZ, 192CZ, 192HB and

192GB (Refer to AMM Task 53-35-11-400-801 and AMM Task 53-35-13-400-802).

(n) If existing, remove the Lower Deck Mobile Crew Rest (LD-MCR) (Refer to AMM

Task 25-75-41-400-801).

(3) Subtask 364033-942-001-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-41-52, Page Block 001

06-41-53, Page Block 001

Task 32-12-00-410-801

Task 36-11-34-400-802

Task 36-22-17-400-801

Task 36-22-17-400-802

Task 52-10-00-410-801

52-30-00, Page Block 201

52-52-00, Page Block 001

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

equipment.

(b) Close the FWD cargo-compartment door 821 and AFT cargo-compartment door

822 (Refer to AMM 06-41-52, Page Block 001 and AMM 52-30-00, Page Block

201).

(c) Close the door 132AZ (Refer to AMM 06-41-53, Page Block 001 and AMM

52-52-00, Page Block 001).

(d) Close the Main Landing Gear (MLG) doors (Refer to AMM Task 32-12-00-410-801).

(e) Do the close-up procedure as specified in the installation of the sensing elements

(Refer to AMM Task 36-22-17-400-801 and AMM Task 36-22-17-400-802).

(f) Do the close-up procedure as specified in the installation of the BMC (FIN 1HA1,

1HA2, 1HA3 and 1HA4) (Refer to AMM Task 36-11-34-400-802).

(g) Close the passenger/crew door(s) (Refer to AMM Task 52-10-00-410-801).

(h) Remove the access platform(s).

(i) Restore the systems and the aircraft to normal operating conditions.

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 545

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@A340

SERVICE BULLETIN

**CONF 004

(1) Subtask 364033-942-201-001 - Close-up

Work Zones and Access Panels

Zone Access/Work location

130 Access Door 821, Door 831

Work location from Frame 20 to Frame 39.1

Panel 132TC

Panel 132CC

Panel 132GC

Panel 132MC

Panel 132RC

Panel 132PC

Panel 132KC

160 Access Door 313AL

Work location Panel 161BC

Panel 161EC

150 Access Door 822

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 25-52-00, Page Block 201

25-54-00, Page Block 201

52-30-00, Page Block 001

(a) In the FWD cargo compartment install the removed ceiling panels (Refer to AMM

25-52-00, Page Block 201).

(b) In the BULK cargo compartment install the removed ceiling panels (Refer to AMM

25-54-00, Page Block 201).

(c) Close the Bulk cargo compartment door (Refer to AMM 52-30-00, Page Block 001).

(2) Subtask 364033-410-004-001 - Install/Close Items Removed/Opened for access

Manpower Resources

Skills NON SPECIFIC

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 546

6

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@A340

SERVICE BULLETIN

References

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

Task 25-21-41-400-801

Task 25-28-41-400-801

Task 25-52-00-400-801

Task 25-53-00-400-801

Task 25-75-41-400-801

Task 53-00-00-400-801

Task 53-00-00-400-802

Task 53-35-11-400-801

Task 53-35-13-400-801

Task 53-35-13-400-802

(a) Between Frame 37.4 and Frame 39.1 in the FWD cargo-compartment, install the

floor panel 132DG (Refer to AMM 06-41-53, Page Block 001 and AMM Task

53-00-00-400-802).

(b) On the RH side, between Frame 38 and Frame 39.1 in the FWD cargocompartment, install (if removed) the sidewall panels 132AX and 132ZW (Refer to

AMM 06-41-53, Page Block 001 and AMM Task 25-52-00-400-801).

(c) On the RH side, between Frame 37.1 and Frame 39.1 in the FWD cargocompartment, install (if removed) the ceiling panels 132TC and 132VC (Refer to

AMM 06-41-53, Page Block 001 and AMM Task 25-52-00-400-801).

(d) At Frame 39.2 in the FWD cargo-compartment, install (if removed) the partition

panels 132DX and 132CX (Refer to AMM 06-41-53, Page Block 001 and AMM

Task 25-52-00-400-801).

(e) At Frame 20 in the FWD cargo-compartment, install the partition panels

131AW and 132CW (Refer to AMM 06-41-53, Page Block 001 and AMM Task

25-52-00-400-801).

(f) On the RH side, between Frame 47 and Frame 53 in the PAX compartment, install

(if removed) the Seats (Refer to AMM Task 25-21-41-400-801).

(g) On the RH side, between Frame 47 and Frame 53 in the PAX compartment, install

(if removed) the Textile Floor Covering (Refer to AMM Task 25-28-41-400-801).

(h) On the RH side, between Frame 47 and Frame 53 in the PAX compartment, install

(if removed) the floor panel 252LG (Refer to AMM Task 53-00-00-400-801).

(i) On the LH side, between Frame 53.2 and Frame 57.1 in the AFT cargo

compartment, install (if removed) the sidewall panels 151EW, 151GW and 151JW

(Refer to AMM 06-41-53, Page Block 001 and AMM Task 25-53-00-400-801).

(j) On the RH side, between Frame 53.2 and Frame 58 in the AFT cargocompartment, install (if removed) the ceiling panels 152BC, 152DC, 152FC

and 152HC (Refer to AMM 06-41-53, Page Block 001 and AMM Task

25-53-00-400-801).

(k) At Frame 53.2 in the AFT cargo-compartment, install the partition panel152CW

(Refer to AMM 06-41-53, Page Block 001 and AMM Task 25-53-00-400-801).

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 547

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@A340

SERVICE BULLETIN

(l) On the LH side of the belly fairing, install (if removed) the panels 191HB,

191FB, 191KB, 193AB, 195CB, 195DB, 197AT, 197BB and 197EB (Refer to

AMM Task 53-35-11-400-801 and AMM Task 53-35-13-400-801 and AMM Task

53-35-13-400-802)

(m) On the RH side of the belly fairing, install the panels 192BZ, 192CZ, 192HB and

192GB (Refer to AMM Task 53-35-11-400-801 and AMM Task 53-35-13-400-802).

(n) If existing, remove the Lower Deck Mobile Crew Rest (LD-MCR) (Refer to AMM

Task 25-75-41-400-801).

(3) Subtask 364033-942-001-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-41-52, Page Block 001

06-41-53, Page Block 001

Task 32-12-00-410-801

Task 36-11-34-400-802

Task 36-22-17-400-801

Task 36-22-17-400-802

Task 52-10-00-410-801

52-30-00, Page Block 201

52-52-00, Page Block 001

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

equipment.

(b) Close the FWD cargo-compartment door 821 and AFT cargo-compartment door

822 (Refer to AMM 06-41-52, Page Block 001 and AMM 52-30-00, Page Block

201).

(c) Close the door 132AZ (Refer to AMM 06-41-53, Page Block 001 and AMM

52-52-00, Page Block 001).

(d) Close the Main Landing Gear (MLG) doors (Refer to AMM Task 32-12-00-410-801).

(e) Do the close-up procedure as specified in the installation of the sensing elements

(Refer to AMM Task 36-22-17-400-801 and AMM Task 36-22-17-400-802).

(f) Do the close-up procedure as specified in the installation of the BMC (FIN 1HA1,

1HA2, 1HA3 and 1HA4) (Refer to AMM Task 36-11-34-400-802).

(g) Close the passenger/crew door(s) (Refer to AMM Task 52-10-00-410-801).

(h) Remove the access platform(s).

(i) Restore the systems and the aircraft to normal operating conditions.

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 548

6

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@A340

SERVICE BULLETIN

**CONF 005

(1) Subtask 364033-942-201-001 - Close-up

Work Zones and Access Panels

Zone Access/Work location

130 Access Door 821, Door 831

Work location from Frame 20 to Frame 39.1

Panel 132TC

Panel 132CC

Panel 132GC

Panel 132MC

Panel 132RC

Panel 132PC

Panel 132KC

160 Access Door 313AL

Work location Panel 161BC

Panel 161EC

150 Access Door 822

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 25-52-00, Page Block 201

25-54-00, Page Block 201

52-30-00, Page Block 001

(a) In the FWD cargo compartment install the removed ceiling panels (Refer to AMM

25-52-00, Page Block 201).

(b) In the BULK cargo compartment install the removed ceiling panels (Refer to AMM

25-54-00, Page Block 201).

(c) Close the Bulk cargo compartment door (Refer to AMM 52-30-00, Page Block 001).

(2) Subtask 364033-410-004-001 - Install/Close Items Removed/Opened for access

Manpower Resources

Skills NON SPECIFIC

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 549

6

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@A340

SERVICE BULLETIN

References

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

Task 25-21-41-400-801

Task 25-28-41-400-801

Task 25-52-00-400-801

Task 25-53-00-400-801

Task 25-75-41-400-801

Task 53-00-00-400-801

Task 53-00-00-400-802

Task 53-35-11-400-801

Task 53-35-13-400-801

Task 53-35-13-400-802

(a) Between Frame 37.4 and Frame 39.1 in the FWD cargo-compartment, install the

floor panel 132DG (Refer to AMM 06-41-53, Page Block 001 and AMM Task

53-00-00-400-802).

(b) On the RH side, between Frame 38 and Frame 39.1 in the FWD cargocompartment, install (if removed) the sidewall panels 132AX and 132ZW (Refer to

AMM 06-41-53, Page Block 001 and AMM Task 25-52-00-400-801).

(c) On the RH side, between Frame 37.1 and Frame 39.1 in the FWD cargocompartment, install (if removed) the ceiling panels 132TC and 132VC (Refer to

AMM 06-41-53, Page Block 001 and AMM Task 25-52-00-400-801).

(d) At Frame 39.2 in the FWD cargo-compartment, install (if removed) the partition

panels 132DX and 132CX (Refer to AMM 06-41-53, Page Block 001 and AMM

Task 25-52-00-400-801).

(e) At Frame 20 in the FWD cargo-compartment, install the partition panels

131AW and 132CW (Refer to AMM 06-41-53, Page Block 001 and AMM Task

25-52-00-400-801).

(f) On the RH side, between Frame 47 and Frame 53 in the PAX compartment, install

(if removed) the Seats (Refer to AMM Task 25-21-41-400-801).

(g) On the RH side, between Frame 47 and Frame 53 in the PAX compartment, install

(if removed) the Textile Floor Covering (Refer to AMM Task 25-28-41-400-801).

(h) On the RH side, between Frame 47 and Frame 53 in the PAX compartment, install

(if removed) the floor panel 252LG (Refer to AMM Task 53-00-00-400-801).

(i) On the LH side, between Frame 53.2 and Frame 57.1 in the AFT cargo

compartment, install (if removed) the sidewall panels 151EW, 151GW and 151JW

(Refer to AMM 06-41-53, Page Block 001 and AMM Task 25-53-00-400-801).

(j) On the RH side, between Frame 53.2 and Frame 58 in the AFT cargocompartment, install (if removed) the ceiling panels 152BC, 152DC, 152FC

and 152HC (Refer to AMM 06-41-53, Page Block 001 and AMM Task

25-53-00-400-801).

(k) At Frame 53.2 in the AFT cargo-compartment, install the partition panel152CW

(Refer to AMM 06-41-53, Page Block 001 and AMM Task 25-53-00-400-801).

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 550

6

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@A340

SERVICE BULLETIN

(l) On the LH side of the belly fairing, install (if removed) the panels 191HB,

191FB, 191KB, 193AB, 195CB, 195DB, 197AT, 197BB and 197EB (Refer to

AMM Task 53-35-11-400-801 and AMM Task 53-35-13-400-801 and AMM Task

53-35-13-400-802)

(m) On the RH side of the belly fairing, install the panels 192BZ, 192CZ, 192HB and

192GB (Refer to AMM Task 53-35-11-400-801 and AMM Task 53-35-13-400-802).

(n) If existing, remove the Lower Deck Mobile Crew Rest (LD-MCR) (Refer to AMM

Task 25-75-41-400-801).

(3) Subtask 364033-942-001-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-41-52, Page Block 001

06-41-53, Page Block 001

Task 32-12-00-410-801

Task 36-11-34-400-802

Task 36-22-17-400-801

Task 36-22-17-400-802

Task 52-10-00-410-801

52-30-00, Page Block 201

52-52-00, Page Block 001

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

equipment.

(b) Close the FWD cargo-compartment door 821 and AFT cargo-compartment door

822 (Refer to AMM 06-41-52, Page Block 001 and AMM 52-30-00, Page Block

201).

(c) Close the door 132AZ (Refer to AMM 06-41-53, Page Block 001 and AMM

52-52-00, Page Block 001).

(d) Close the Main Landing Gear (MLG) doors (Refer to AMM Task 32-12-00-410-801).

(e) Do the close-up procedure as specified in the installation of the sensing elements

(Refer to AMM Task 36-22-17-400-801 and AMM Task 36-22-17-400-802).

(f) Do the close-up procedure as specified in the installation of the BMC (FIN 1HA1,

1HA2, 1HA3 and 1HA4) (Refer to AMM Task 36-11-34-400-802).

(g) Close the passenger/crew door(s) (Refer to AMM Task 52-10-00-410-801).

(h) Remove the access platform(s).

(i) Restore the systems and the aircraft to normal operating conditions.

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 551

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF ALL

B

G

H

K

A

FR39

FR45

FR53.5

FR56

(2) 98HF

(9)

(8)

25HF

24HF

(3)

(6)

99HF

100HF

(4)

(5) 102HF

101HF

(7) 23HF

Z190

BEFORE

A (1) 97HF

F_SB_364033_5_BAAA_01_01

Figure A-FBAAA - Sheet 01

Removal of the Sensing Elements between FR39 and FR55 on the LH side

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 552

6

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@A340

SERVICE BULLETIN

**CONF ALL

SCREW WASHER CLAMP SLEEVE SPACER

FR44

FR40

FR40.1

FR40.2

FR40.3

FR41

FR42

FR43

FR40.3 FR41 FR42 FR43

FR40.2

FR40.1

(15)

(10)

(11)

(10)

(15)

(11)

C

K

(21) (14) (86) (13) (16)

(91) (14) (86) (13) (16)

(20) (14) (86) (13)

F

E

D

D

D

F

D

F

D

E

E

E

(2) 98HF

(1)

C

K

BELLY FAIRING TRACE

FUSELAGE TRACE

97HF

B

F_SB_364033_5_BAAA_02_00

Figure A-FBAAA - Sheet 02

Removal of the Sensing Elements between FR39 and FR55 on the LH side

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 553

6

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@A340

SERVICE BULLETIN

**CONF ALL

SCREW WASHER CLAMP SLEEVE SPACER

BELLY FAIRING TRACE

FUSELAGE TRACE

FR51

FR50

FR49

FR48

FR47

FR46

FR45

FR45

FR46

FR47

FR48

(11)

(10)

(15)

L

(21) (14) (86) (13) (16)

(20) (14) (86) (13)

F

D

F

D

D

F

F

L

F

(6)

(4) 101HF

100HF

(3) 99HF

F

D

F

D

F

F

L

G

F_SB_364033_5_BAAA_03_01

Figure A-FBAAA - Sheet 03

Removal of the Sensing Elements between FR39 and FR55 on the LH side

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 554

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF ALL

SCREW WASHER CLAMP SLEEVE SPACER

FUSELAGE TRACE

(11)

(10)

(15)

L

(91)

(93)

(21)

(20)

(14)

(14)

(14)

(14)

(86)

(86)

(86)

(86)

(13)

(13)

(13)

(13)

(16)

(16)

(16)

(18)

(16)

J

N

F

FR51 D

FR52

FR53

FR53.1

FR53.2

FR53.3

FR53.4

FR53.5

FR53.6

(4)

(7) 23HF

D

F

D

F

F

D

L

(5) 102HF

FR53.2

FR52

FR53

FR53.1

FR53.5

FR53.4

FR53.3

L

L

BELLY FAIRING TRACE

J

F

D F

F

101HF

N

H

F_SB_364033_5_BAAA_04_01

Figure A-FBAAA - Sheet 04

Removal of the Sensing Elements between FR39 and FR55 on the LH side

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 555

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF ALL

SCREW WASHER CLAMP SLEEVE SPACER

FUSELAGE TRACE

(11)

(10)

(15)

L

(15)

P

(91)

(21)

(20)

(14)

(14)

(14)

(86)

(86)

(86)

(13)

(13)

(13)

(16)

(16)

J (16)

F

D

FR53.6

FR53.7

FR53.8

FR53.9

FR54

FR55

P

F

D

F

D

D

D

D

J

J

D

(8)

(9) 25HF

24HF

D

K

F_SB_364033_5_BAAA_05_00

Figure A-FBAAA - Sheet 05

Removal of the Sensing Elements between FR39 and FR55 on the LH side

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 556

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF ALL

A

(113)

(112)

(114)

FR53.5

FR53.6

Z150

F_SB_364033_5_BBAA_01_00

B

A

B

Figure A-FBBAA - Sheet 01

Removal/Installation of the Ducts between FR53.6 and FR53.7 on the LH side (for Access)

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 557

6

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@A340

SERVICE BULLETIN

**CONF ALL

Z150

FR53.3

FR54

FR53.5

FR53.6

AFTER

A

B

D

F

A

B

C E

F_SB_364033_5_BCAA_01_02

Figure A-FBCAA - Sheet 01

Drilling of a New Hole in the Structure between FR53.5 and FR53.6 on the LH side and Installation of

Sensing Elements

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 558

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF ALL

SKIN PANEL NOT SHOWN

DIA. 24 mm (0.944 in)

RADIUS 2 mm (0.078 in)

13.5 mm MIN. (0.531 in)

 13.7 mm MAX. (0.539 in)

2 mm MIN. (0.078 in)

3 mm MAX. (0.118i n)

FWD

A

A

C

A A

207 mm

(8.149 in)

NEW

HOLE

EXISTING

HOLE

71 mm

(2.795 in)

F_SB_364033_5_BCAA_02_02

Figure A-FBCAA - Sheet 02

Drilling of a New Hole in the Structure between FR53.5 and FR53.6 on the LH side and Installation of

Sensing Elements

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 559

6

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@A340

SERVICE BULLETIN

**CONF ALL

169

169

155

1S 2SG

REPLACED SENSING NEW SENSING

FWD

D

14

18

168

EXISTING SENSING

169

(155)

169

175

(175)

174

(174)

175

310HF

138HF

137HF

309HF

27

27

3503VS

3593VS

F_SB_364033_5_BCAA_03_02

Figure A-FBCAA - Sheet 03

Drilling of a New Hole in the Structure between FR53.5 and FR53.6 on the LH side and Installation of

Sensing Elements

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 560

6

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@A340

SERVICE BULLETIN

**CONF ALL

EXISTING SENSING NEW SENSING

92

27

133

FWD

E

182

F_SB_364033_5_BCAA_04_01

Figure A-FBCAA - Sheet 04

Drilling of a New Hole in the Structure between FR53.5 and FR53.6 on the LH side and Installation of

Sensing Elements

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 561

6

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@A340

SERVICE BULLETIN

**CONF ALL

EXAMPLE OF INSTALLATION OF WIRE−LOCK PN MS20995C32 (ITEM ) 27

F

F_SB_364033_5_BCAA_05_00

Figure A-FBCAA - Sheet 05

Drilling of a New Hole in the Structure between FR53.5 and FR53.6 on the LH side and Installation of

Sensing Elements

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 562

6

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@A340

SERVICE BULLETIN

**CONF ALL

Z190

FR47

FR44

FR40.2

(116)

(115)

F_SB_364033_5_BDAA_01_00

A B

A

B

Figure A-FBDAA - Sheet 01

Removal/Installation of the Ducts between FR44 and FR47 on the LH side (for Access)

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 563

6

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@A340

SERVICE BULLETIN

**CONF ALL

A

B

FR44

(119)

(123)

(124)

B

B

(117)

117

(120)

120

(119)

(124)

(121)

(118)

118

(119)

(122)

BEFORE/AFTER

Z190

C

C A

A

B

F_SB_364033_5_BEAA_01_00

A

Figure A-FBEAA - Sheet 01

Replacement of the Web Assy at FR44 on the LH side

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 564

6

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@A340

SERVICE BULLETIN

**CONF ALL

FWD

FWD

FWD

A A

B B

(118)

118

(117)

117

(123)

(117)

117

C C

MAT. NO. 09−016B

MAT. NO. 09−019B

F_SB_364033_5_BEAA_02_00

01

02

NOTE:

02

01

02

02

02

Figure A-FBEAA - Sheet 02

Replacement of the Web Assy at FR44 on the LH side

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 565

6

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@A340

SERVICE BULLETIN

**CONF ALL

A

Z150

FR53.3

FR54

FR53.5

FR53.6

96

C

B

FWD

B

A

F_SB_364033_5_BFAA_01_00

STGR32

STGR33

STGR34

STGR36 STGR35

Figure A-FBFAA - Sheet 01

Installation of a New Bracket between FR53.5 and FR53.6

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 566

6

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@A340

SERVICE BULLETIN

**CONF ALL

FR53.5

197 mm

(7.75 in)

96

FR53.6

D

F

W

D

D

C

19.8 mm

(0.78 in)

ASNA2050DCJ3215 3.25 mm

(0.128 in)

3.35 mm

(0.132 in)

HOLE

SYMBOL ITEM PN DESCRIPTION

HOLE DIAMETER

MIN MAX

RIVET

VIEW LOOKING DOWN

STGR23

STGR33

STGR34

01 APPLY MAT. No. 09−005A TO THE INTERFACE

02 SEALANT BEAD WITH MAT No. 09−016B.

03 WET INSTALL THE FASTENERS WITH MAT. No. 09−005A.

NOTE:

OF THE NEW BRACKET AND THE STRUCTURE.

03

96

01

02

97

F_SB_364033_5_BFAA_02_01

Figure A-FBFAA - Sheet 02

Installation of a New Bracket between FR53.5 and FR53.6

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 567

6

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@A340

SERVICE BULLETIN

**CONF ALL

A

98

99

C

Z190

B

FR44

A

A A

VIEW LOOKING FORWARD

B C

F_SB_364033_5_BGAA_01_00

184.5 mm

(7.26 in)

Figure A-FBGAA - Sheet 01

Installation of Two New Brackets at FR44

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 568

6

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@A340

SERVICE BULLETIN

**CONF ALL

99

98

F

W

D

A A

ASNA2050DCJ3215 3.25 mm

(0.128 in)

3.35 mm

(0.132 in)

HOLE

SYMBOL ITEM PN DESCRIPTION

HOLE DIAMETER

MIN MAX

RIVET

01 APPLY MAT. No. 09−005A TO THE INTERFACE

02 SEALANT BEAD WITH MAT No. 09−016B.

03 WET INSTALL THE FASTENERS WITH MAT. No. 09−005A.

NOTE:

OF THE NEW BRACKET AND THE STRUCTURE.

03

01

02

01

02

109 mm

(4.29 in)

97

F_SB_364033_5_BGAA_02_01

Figure A-FBGAA - Sheet 02

Installation of Two New Brackets at FR44

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 569

6

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@A340

SERVICE BULLETIN

**CONF ALL

A Z192

B

FR39

FR40

A

(125)

(126)

(127) B

F_SB_364033_5_BPAA_01_00

Figure A-FBPAA - Sheet 01

Removal/Installation of the Ducts Between FR39 and FR40 for Access

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 570

6

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@A340

SERVICE BULLETIN

**CONF ALL

A Z190

FR37

FR39.1

FR39.2

FR58

A B

F_SB_364033_5_BNAA_01_01

Figure A-FBNAA - Sheet 01

Installation of the Supports for the New Harness

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 571

6

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@A340

SERVICE BULLETIN

**CONF ALL

FR38 FR39 FR39.1 FR39.2 FR40

STGR36

STGR38

STGR40

STGR42

STGR44

STGR46

STGR48

STGR50

STGR52

STGR54

STGR54

STGR52

STGR50

STGR48

STGR46

STGR44

STGR42

STGR40

STGR38

STGR36

A/C CL

FWD B

2HR 2M

1M

2MK/2M1K

2SK/2S1K

2MK/2M1K

2S 2M

2SK/2S1K

1HR

1M

1M

2SG

1M−2M

1M 2M

1SK/1S2K

1MK/1M2K

1M

1S

1S

2SG

1SK/1S2K

1M 1S

1MK/1M2K

3501VS

3591VS J

H

F G

C D E

F_SB_364033_5_BNAA_02_01

Figure A-FBNAA - Sheet 02

Installation of the Supports for the New Harness

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 572

6

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@A340

SERVICE BULLETIN

**CONF ALL

HOLE

SYMBOL ITEM PN DESCRIPTION

HOLE DIAMETER

MIN MAX

3.25 mm

(0.128 in)

3.35 mm

(0.132 in) 97 ASNA2050DCJ3215 RIVET

F

BEFORE AFTER

AFTER

HEAD ON HIDDEN SIDE

FASTENER NOT AFFECTED

F

01 APPLY MAT. No. 09−005A TO THE INTERFACE

02 WET INSTALL THE FASTENERS WITH MAT. No. 09−013B.

NOTES:

OF THE PARTS AND THE STRUCTURE.

02

FR39.1

(88)

(97)

FR39.1

97

220 mm

(8.66 in)

73 mm

(2.87 in)

FR39.1

(88)

97

STGR37

STGR38

01

C D

E

FWD FWD

FWD

F_SB_364033_5_BNAA_03_02

Figure A-FBNAA - Sheet 03

Installation of the Supports for the New Harness

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 573

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF ALL

HOLE

SYMBOL ITEM PN DESCRIPTION

HOLE DIAMETER

MIN MAX

3.25 mm

(0.128 in)

3.35 mm

(0.132 in) 97 ASNA2050DCJ3215 RIVET

F

BEFORE AFTER

AFTER

HEAD ON HIDDEN SIDE

FASTENER NOT AFFECTED

F

01 APPLY MAT. NO. 09−005A TO THE INTERFACE

02 WET INSTALL THE FASTENERS WITH MAT. NO. 09−013B.

NOTES:

OF THE PARTS AND THE STRUCTURE.

02

FR39.2

(89) (97)

STGR46

POSITIONING

FR39.2

97

97

64

STGR46

HOLE

FR39.2

STGR46

STGR47

486 mm

(19.13 in)

218 mm

(8.58 in)

50 mm

(1.97 in)

56.5 mm

(2.22 in) 63

63

97

97

01

01

F G

H

FWD FWD

FWD

01

F_SB_364033_5_BNAA_04_03

Figure A-FBNAA - Sheet 04

Installation of the Supports for the New Harness

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 574

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF ALL

VIEW LOOKING FORWARD

BELLY−FAIRING AREA

FUSELAGE CONTOUR

Y2390

Z−2250

HOLE

SYMBOL ITEM PN DESCRIPTION

HOLE DIAMETER

MIN MAX

3.25 mm

(0.128 in)

3.35 mm

(0.132 in) 97 ASNA2050DCJ3215 RIVET

F

58.4 mm

(2.30 in)

13.7 mm

(0.54 in)

FR39.1

65

97

STGR38

STGR39

STGR40

HEAD ON HIDDEN SIDE

FASTENER NOT AFFECTED

F

01 APPLY MAT. NO. 09−005A TO THE INTERFACE

02 WET INSTALL THE FASTENERS WITH MAT. NO. 09−013B.

NOTES:

OF THE PARTS AND THE STRUCTURE.

01

02

F

W

D

K

J

K

F_SB_364033_5_BNAA_05_03

Figure A-FBNAA - Sheet 05

Installation of the Supports for the New Harness

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 575

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF ALL

A

FR56

FR53.5

A

FR45

FR39

101

102

113

100

303HF

98HF

302HF

97HF

Z190

B

F_SB_364033_5_BHAA_01_02

Figure A-FBHAA - Sheet 01

Installation of the New Sensing Elements between FR39 and FR44 on LH side

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 576

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF ALL

FR44

FR43

FR42

FR41

FR40.3

FR40.2

FR40.1

FR40

FR40.2

FR40.3

FR41

FR42

FR43

FR40.1

FR40

BELLY FAIRING TRACE

FUSELAGE TRACE

114 97HF

101 303HF

113 302HF

102 98HF

L

J

C

G

E

30

11

TYPICAL

P

OR

15

27

15

27

27

15 15

B

Q

F_SB_364033_5_BHAA_02_01

Figure A-FBHAA - Sheet 02

Installation of the New Sensing Elements between FR39 and FR44 on LH side

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 577

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF ALL

R

C C

C C

C C

H

D

B

B

P Q

P Q

FWD

FWD

C VIEW LOOKING AFT

C

C

C

C

C

B

B

FR39.2

FR40

C

D

113

114

302HF

F 97HF

E

13

14

20

10

10

13

14

20

14

20

13

14

16

21

10

14

20 13

14

20

10

78

F

33

32

35

34

30

32 33

30

G

H

FR40.2 FR40.1 FR40

F_SB_364033_5_BHAA_03_01

Figure A-FBHAA - Sheet 03

Installation of the New Sensing Elements between FR39 and FR44 on LH side

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 578

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF ALL

13

10

14

20

18

10

14 13

24

16

13

10

14

21

FR41

FR40.3

FR40.2

K

101 303HF

FWD

D

D

A

A

A

A

A

A

B

B

FR44 FR43 FR42

N

FWD

10 13

14

20

13

14

20

13 10

14

20

14

20

14

13 10

14

16

13

10

70

13 10

14

18

24

18

13

14

24

18

13

10

10

14

24

79

14

29

10

13 14

29

TYPICAL

R

S

N

K

J

L

A A B B C C

D D

10

S

A

A

A

A

A

A

A

A

A

A

102 98HF

21 20

F_SB_364033_5_BHAA_04_00

Figure A-FBHAA - Sheet 04

Installation of the New Sensing Elements between FR39 and FR44 on LH side

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 579

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF ALL

A Z190

FR56

FR53.5

FR39

AFTER

114

103 105

103

100HF

99HF 305HF

304HF

FR45

A

B

F_SB_364033_5_BJAA_01_02

Figure A-FBJAA - Sheet 01

Installation of the New Sensing Elements between FR44 and FR50 on LH side

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 580

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF ALL

FR48

FR47

FR46

FR45

FR51

FR50

FR49

FR48

FR47

FR46

FR45

N

L

F

C

H

K

FUSELAGE TRACE

BELLY FAIRING TRACE

114 100HF

105 305HF

103 99HF

30

11

TYPICAL INSTALLATION

B

OR

27

15

27 15

27

15

15

T

304HF 103

S

TYPICAL INSTALLATION

F_SB_364033_5_BJAA_02_01

Figure A-FBJAA - Sheet 02

Installation of the New Sensing Elements between FR44 and FR50 on LH side

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 581

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF ALL

39

38 36

37

39

38

40

41

C

C

E

E

C

C

E

E

Q

C

C

C

C

FR45

FR44

VIEW LOOKING FORWARD

FR46

VIEW LOOKING FORWARD

VIEW LOOKING AFT

FWD

FWD

FWD

FWD

FWD

2POS

36

37

103

103

99HF

304HF

E

J

13 13 13 10 13

14

20

14

16

21

14

18

23 14

20

14

20

G

2POS

10

13

14

20

34

35

D

E

J

H

D

C

S T

N

Q

Q

30 30

C

C

10 10

81

10

10

13

14

20

T

K

S T

G

C

C

F

F_SB_364033_5_BJAA_03_02

Figure A-FBJAA - Sheet 03

Installation of the New Sensing Elements between FR44 and FR50 on LH side

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 582

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF ALL

P

Q

105

114

G

G

A

A A

A

C

C

C

C

FWD

L

P

R

Q R

TYPICAL INSTALLATION

A

A

A

A

A

A

FR50 FR47 FR48 FR49

10 13

14

20

14

20

14

20

13 13 10 10

14

20

79

14

29

80

14

29 13

10

13

14

20

10

16

10

13

14

21 17

10

13

14

26

16

18

10

13

14

19

A A C C

E E G G

100HF

305HF

F_SB_364033_5_BJAA_04_01

Figure A-FBJAA - Sheet 04

Installation of the New Sensing Elements between FR44 and FR50 on LH side

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 583

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF ALL

B

A Z190

FR56

FR53.5

FR45

FR39

AFTER

106

107

102HF

307HF

106

106

101HF

306HF

108

104

23HF

308HF

A

F_SB_364033_5_BKAA_01_01

Figure A-FBKAA - Sheet 01

Installation of the New Sensing Elements between FR50 and FR53.6 on LH side

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 584

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF ALL

FR52

FR53

FR53.1

FR53.2

FR53.4

FR53.5

307HF

306HF

101HF

FUSELAGE TRACE

FR51

FR52

FR53

FR53.1

FR53.2

FR53.3

FR53.4

FR53.5

FR53.6

106

106

107 23HF 108

104 308HF

M

C

OR

G

H

11

15

27

15

27

27

15

30

25

OR

TYPICAL

B

X

Y

FR53.3

BELLY FAIRING TRACE

106 102HF

15

F_SB_364033_5_BKAA_02_01

Figure A-FBKAA - Sheet 02

Installation of the New Sensing Elements between FR50 and FR53.6 on LH side

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 585

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF ALL

J K

FR53.2 FR53.3 FR53.4

A

A A

A

D

A

A

F

FR51 FR52 FR53 FR53.1

C

C

C

C

C

C

14

20

14

20 14

20 70

10 10 13 13 10

K

72

10 13

14

16

21

10 13 10 10 13

14

20

75 14

16

21

14

16

21

10 13 10 13

E

82

F

14

20

14

16

21

14

20

10 13 10 13

14

20

14

16

21

74

J

14

16

21

14

20

10 13

10 13

83

73

14

20

L

13

A

A

A

A

A

A

FR53.2

FWD

C X Y

42

43

30

40

41

101HF 106

306HF 106

G

14

20

14

20

D

L

H

13

14

29

14

20

E

F_SB_364033_5_BKAA_03_00

Figure A-FBKAA - Sheet 03

Installation of the New Sensing Elements between FR50 and FR53.6 on LH side

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 586

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF ALL

10 13

14

20

77

14

29

14

29

13 84 10

14

20

14

20

14

22

28

10

10 13

13

14

20

76

STGR36

STGR37

STGR38

STGR39

STGR40

STGR41

STGR42

STGR43

STGR44

STGR45

STGR46

STGR47

STGR48

STGR49

STGR50

FR53.5 FR53.6

C

C

C

C

C

C

T

FWD

N

43

42

45

44

30

X Y

R

S

T

C

C

C C

C

C

B

B

N

P

Q

R

C

C

T

107

106

307HF

102HF

104

108

308HF

23HF

VIEW LOOKING FORWARD

M

79

14

29

13

10

14

29

U

T

U

18

10

14 13

24

16

13

10

14

21

13

10

14

20

A A B B C C

P

Q

45

44

25

X

S

Y

F_SB_364033_5_BKAA_04_00

Figure A-FBKAA - Sheet 04

Installation of the New Sensing Elements between FR50 and FR53.6 on LH side

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 587

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF ALL

B

A

FR56

FR53.5

FR45

FR39

AFTER

112

111

109

110

312HF

25HF

24HF

311HF

Z190

A

F_SB_364033_5_BLAA_01_01

Figure A-FBLAA - Sheet 01

Installation of the New Sensing Elements between FR53.6 and FR55 on LH side

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 588

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF ALL

OR

27

15

27 15

27

15

30

11

P

J

C

24HF 109

312HF

TYPICAL

N

FUSELAGE TRACE

112

FR53.6

FR53.7

FR53.8

FR53.9

FR54

FR55

B

111 25HF

110 311HF

15

F_SB_364033_5_BLAA_02_00

Figure A-FBLAA - Sheet 02

Installation of the New Sensing Elements between FR53.6 and FR55 on LH side

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 589

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF ALL

N F

89

30

91

90 88

FWD

H

27 J

J

10

14

20

13

14

20

93

10

14

20

13

F

14

29

79

13

10

14

29

G

FWD

D

D

A A

H

H

13

14

20

86

D

VIEW LOOKING FORWARD

G

E

C

C

D

D

B

B

G

G

D

D

B B

B B

D

D

D D

B B

D

D E

112 312HF

111 25HF

24HF 108

110 311HF C

FWD

FWD

92

27

85

J J H H

55°

27

D

D

D

F

F_SB_364033_5_BLAA_03_00

E

E

Figure A-FBLAA - Sheet 03

Installation of the New Sensing Elements between FR53.6 and FR55 on LH side

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 590

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF ALL

FR53.9 FR55

K L

D FR54

D

D

D

14

16

94

14

20

14

20

10 10

13

14

16

94

13

95

13

10

14

16

94

10

14

16

94

14

16

94

13

13

10

J

K L

13

10

14

87

17

13

10

14

26

17

13

10

14

26

10

14

20 13

13

14

21

10

16

14

87

13

86

18 13

10

14

20

13

10

14

20 13

E E G G

D D

C C

B B

A A

18

70

F_SB_364033_5_BLAA_04_00

Figure A-FBLAA - Sheet 04

Installation of the New Sensing Elements between FR53.6 and FR55 on LH side

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 591

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF ALL

A

3520VP

3672VC

3506VC

3520VC

NEW HARNESS 2SG

SPARES CONDUITS

2S

A

301HF

FR37

FR39.1

FR39.2

FR56

FR57

FR58

Z190

B C

F_SB_364033_5_BMAA_01_01

Figure A-FBMAA - Sheet 01

Installation of the New Harness 2SG

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 592

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF ALL

FR38 FR39 FR39.1 FR39.2 FR40

STGR36

STGR38

STGR40

STGR42

STGR44

STGR46

STGR48

STGR50

STGR52

STGR54

STGR54

STGR52

STGR50

STGR48

STGR46

STGR44

STGR42

STGR40

STGR38

STGR36

A/C CL

BEFORE

2HR 2M

1M 2S

2MK/2M1K

2SK/2S1K

2MK/2M1K

2S 2M

2SK/2S1K

1HR

1M

1M−2M

1M 2M

1SK/1S2K

1MK/1M2K

1M

1S

1S

1SK/1S2K

1M 1S

1MK/1M2K

3501VS

1M

FWD B

F

D

H

J

K

M

N

Q

Y

A E

A C

A A

W

T

F_SB_364033_5_BMAA_02_01

Figure A-FBMAA - Sheet 02

Installation of the New Harness 2SG

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 593

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF ALL

FR38 FR39 FR39.1 FR39.2 FR40

STGR36

STGR38

STGR40

STGR42

STGR44

STGR46

STGR48

STGR50

STGR52

STGR54

STGR54

STGR52

STGR50

STGR48

STGR46

STGR44

STGR42

STGR40

STGR38

STGR36

A/C CL

AFTER

2HR

2M

1M 2S

2MK/2M1K

2SK/2S1K

2MK/2M1K

2S 2M

2SK/2S1K

1HR

1M

1M

2SG

1M−2M

1M 2M

1SK/1S2K

1MK/1M2K

1M

1S

1S

2SG

1SK/1S2K

1M 1S

1MK/1M2K

NEW HARNESS

NEW HARNESS

NEW HARNESS

3501VS

3591VS

FWD C

G

A L

A M

L

A N

P

R

Z

S U

V

X

A B

A D

A F

A G

E

F_SB_364033_5_BMAA_03_02

Figure A-FBMAA - Sheet 03

Installation of the New Harness 2SG

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 594

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF ALL

VIEW LOOKING FORWARD

BEFORE

D

1S

Y2390

Z−2250

1S

FUSELAGE CONTOUR

BELLY−FAIRING AREA

3501VS

FR39.1

STGR38

STGR39

STGR40

A

A

A

A

A

A

A

A

A

A

A A

A

A

A Q

A P

FWD A P

F_SB_364033_5_BMAA_04_02

Figure A-FBMAA - Sheet 04

Installation of the New Harness 2SG

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 595

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF ALL

VIEW LOOKING FORWARD

AFTER

E

2SG

1S

Y2390

Z−2250

2SG

1S

FUSELAGE CONTOUR

BELLY−FAIRING AREA

3591VS

3501VS

FR39.1

STGR38

STGR39

STGR40

C C

B

B

B

B

B

B

B B

B

B

B

B

B

B

A J

A J

A K

FWD

F_SB_364033_5_BMAA_05_02

Figure A-FBMAA - Sheet 05

Installation of the New Harness 2SG

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 596

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF ALL

BEFORE

AFTER

VIEW LOOKING FORWARD

VIEW LOOKING FORWARD

A A

B B C C

1S

(130)

(131)

(150)

2SG

1S

150

152

131

154

151

(150)

2SG

1S

151 131

154

65

152

150

150

FWD

F_SB_364033_5_BMAA_06_02

Figure A-FBMAA - Sheet 06

Installation of the New Harness 2SG

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 597

6

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@A340

SERVICE BULLETIN

**CONF ALL

BEFORE

FWD

A H

G

G

F

F

F_SB_364033_5_BMAA_07_00

Figure A-FBMAA - Sheet 07

Installation of the New Harness 2SG

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 598

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF ALL

AFTER

A K

H

H

FWD

2SG

J

J

F_SB_364033_5_BMAA_08_02

Figure A-FBMAA - Sheet 08

Installation of the New Harness 2SG

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 599

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF ALL

VIEW LOOKING FORWARD

BEFORE AFTER

BEFORE

AFTER

F G

F F

G G

H H J J

1S

2SG

1M

1S

1S

(135) (134)

(136)

(137)

(150)

(130)

(131)

(150)

152

131

154

151

150

1S

1S

2SG

1S

2SG

1M

(135) (134)

152

150

131

154 151

(132)

(133) (155)

151

(155)

150

152

131

154

FWD

FWD FWD

FWD

FWD

F_SB_364033_5_BMAA_09_02

Figure A-FBMAA - Sheet 09

Installation of the New Harness 2SG

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 600

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF ALL

STGR45

1M

STGR45

1M

FR39.1

FR39.1

BEFORE

H AFTER

A L

K K

M M

L L

N N

FWD

FWD

F_SB_364033_5_BMAA_10_00

Figure A-FBMAA - Sheet 10

Installation of the New Harness 2SG

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 601

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF ALL

BEFORE

AFTER

K K

M M

OR

OR

1S 1M

1M

2SG

1S 1M

1M

(135)

(138)

(151)

(134)

(152)

(153)

(154)

(151)

(134)

(152)

150

131

154

(135)

(138)

1S

1M

1M

2SG

1S 1M

1M

1M

1M

(135)

(138)

(151) (153)

(154)

(134)

(152)

(139)

131

(135)

(139)

(134)

173

(138)

150

163

154

FWD

FWD

F_SB_364033_5_BMAA_11_02

Figure A-FBMAA - Sheet 11

Installation of the New Harness 2SG

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 602

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF ALL

BEFORE

AFTER

L L

N N

1S

1M

2SG

1S 1M

(135) (134)

(153)

(130)

(134)

152

150

151 (135)

131

154

FWD

FWD

F_SB_364033_5_BMAA_12_02

Figure A-FBMAA - Sheet 12

Installation of the New Harness 2SG

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 603

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF ALL

OR

OR

BEFORE

AFTER

J

A M

STGR49

STGR48

STGR47

Q Q

P P

FR39.2 FR39.1

STGR49

STGR48

STGR47

FR39.2 FR39.1

FWD

FWD

S S

R R

STGR49

STGR48

STGR47

P P

FR39.2 FR39.1

STGR49

STGR48

STGR47

FR39.2 FR39.1

R R

F_SB_364033_5_BMAA_13_02

Figure A-FBMAA - Sheet 13

Installation of the New Harness 2SG

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 604

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF ALL

OR

OR

BEFORE

AFTER

P P

R R

1S

1M

1M

2SG

1S 1M

1M

(135)

(139)

(151)

(153)

(154)

(152)

(134)

(135)

(139)

151

(134)

(152)

150

131

154

1S

1M

1M

1M

(135)

(138)

(151) (153)

(154)

(134)

(152)

(139)

2SG

1S 1M

1M

1M

131

(135)

(139)

(134)

173

(138)

150

163

154

FWD

FWD

F_SB_364033_5_BMAA_14_02

Figure A-FBMAA - Sheet 14

Installation of the New Harness 2SG

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 605

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF ALL

AFTER

BEFORE

Q Q

S S

OR

OR

1S

1M

1M

2SG

FWD

1M

1S

1M

(134)

(139) (152)

(135)

(151)

(151)

150 (152) (139)

(134) (135)

(153)

(154)

153

154

FWD

1S

1M

1M

2SG

1M

1S

1M

(134)

(139) (152)

(135)

(144)

163

150 173 (139)

(134) (135)

(153)

(154)

153

154

1M

(138)

1M

(138)

F_SB_364033_5_BMAA_15_02

Figure A-FBMAA - Sheet 15

Installation of the New Harness 2SG

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 606

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF ALL

AFTER

K

L

BEFORE

FUSELAGE CONTOUR 1M

1M

2SG

FWD

FUSELAGE CONTOUR

(138)

(132)

(153)

(138)

150

151

152

131

154

FWD

F_SB_364033_5_BMAA_16_02

Figure A-FBMAA - Sheet 16

Installation of the New Harness 2SG

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 607

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF ALL

BEFORE AFTER

M

BEFORE AFTER

T T U U

A N

STGR54

T T

FWD

1M

1M

(140)

(141)

(138)

(153)

(154)

FWD

1M

1M

2SG

STGR54

U U

FWD

(140)

(141)

150

(138)

131

154

FWD

F_SB_364033_5_BMAA_17_02

Figure A-FBMAA - Sheet 17

Installation of the New Harness 2SG

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 608

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF ALL

BEFORE AFTER

BEFORE AFTER

AFTER

N P

R

S

Q

1M

1M

(138)

(142)

(153)

(138)

(142)

(153)

FWD

FWD

2SG

1M

1M

2SG

(138)

152

150

151

131

154

150 (138)

153

158

FWD

FWD

131

159

150

FWD

2SG

63

F_SB_364033_5_BMAA_18_02

Figure A-FBMAA - Sheet 18

Installation of the New Harness 2SG

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 609

6

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@A340

SERVICE BULLETIN

**CONF ALL

V

AFTER

2S

2M

2SG

2SG V V

W

W

V V

1S

179

141

171

172

FUSELAGE CONTOUR

2S

179

171

172

141

64 180 180

181 181

W W

2M

FUSELAGE CONTOUR

134 2S

135

163

16

152

153

154

64

FWD

NOTE:

ONLY ONE CONFIGURATION SHOWN.

EQUIPMENT MAY DIFFER DEPENDING ON AIRCRAFT CONFIGURATION.

F_SB_364033_5_BMAA_19_04

Figure A-FBMAA - Sheet 19

Installation of the New Harness 2SG

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 610

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF ALL

BEFORE AFTER

T U

W X

Y

Z

2S

2M

FUSELAGE CONTOUR

2MK/2M1K

(135)

(134)

(136)

(153)

2S

2M

FUSELAGE CONTOUR

(135)

(134)

(136)

(153)

FUSELAGE CONTOUR

(133)

(143)

2SK/2S1K

(155) (155)

2S

2M

2SK/2S1K

FUSELAGE CONTOUR

151 141

165

(135)

(134)

153

154

2M

FUSELAGE CONTOUR

2SG

2S

2SG

FUSELAGE CONTOUR

2MK/2M1K

(155) (155)

152

22

163

150 131

154

157

16

152

(135)

176

153

154

177

178

F_SB_364033_5_BMAA_20_02

Figure A-FBMAA - Sheet 20

Installation of the New Harness 2SG

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 611

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF ALL

BEFORE AFTER

(153)

A A A B

A D A C

A E A F

2S

2M

FUSELAGE CONTOUR

(135)

(134)

(136)

(153)

2S

2M

FUSELAGE CONTOUR

(135)

(134)

(136)

(153)

2M

(135)

(142)

(88)

FWD

FWD

FWD

2M

FUSELAGE CONTOUR

151

(135)

153

154

FUSELAGE CONTOUR

2SG

2S

176

18

2SG

2S

176

2M

(135) 153

167

2M

(135)

153

158

FWD

(88)

177

177

178

178

FWD

FWD

F_SB_364033_5_BMAA_21_05

Figure A-FBMAA - Sheet 21

Installation of the New Harness 2SG

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 612

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF ALL

(4 POS) (4 POS)

(4 POS)

(3 POS)

14

170

(184)

(183)

166

(184)

(14)

(170)

(166)

184

183

184

NOTE:

ONLY ONE CONFIGURATION SHOWN.

EQUIPMENT MAY DIFFER DEPENDING ON AIRCRAFT CONFIGURATION.

A H

FWD A G

A H

F_SB_364033_5_BMAA_22_01

Figure A-FBMAA - Sheet 22

Installation of the New Harness 2SG

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 613

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF ALL

Figure A-FCAAA - Sheet 01

Modification of the Wiring in the Main Rack 800VU

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 614

6

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@A340

SERVICE BULLETIN

**CONF ALL

Figure A-FCAAA - Sheet 02

Modification of the Wiring in the Main Rack 800VU

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 615

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF ALL

Figure A-FCAAA - Sheet 03

Modification of the Wiring in the Main Rack 800VU

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 616

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF ALL

END1 LEAD END2

Instructions Zone or

Panel Elec.Ident. Term Terminal P/N

Wire

Ident. Co Rte Gauge

Lenght

mm Inch

Zone or

Panel Elec.Ident. Term Terminal P/N

L

i

n

e

 1 851VU 1HA1−AB 12A 3612−0097 1M CF24 851VU 2901VT 65E D

 2 851VU 2901VT 65F 3612−0072 1M CF24 801VU 2615VC 19 D

 3 851VU 2901VT 65M 3612−0078 1M CF24 852VU 1HA2−AA 11D D

 4 851VU 2901VT 65V 3612−0098 1M CF24 852VU 1HA3−AB 12A D

 5 851VU 2901VT 65N 3612−0099 1M CF24 852VU 1HA4−AB 12A D

 6

 7

 8

 9 851VU 2901VT 54X EN3155−016M2222 3612−0078 1M CF24 2000 80 851VU 1HA2−AA 11D E0170FA2200 (a) A

10 851VU 2901VT 54S EN3155−016M2222 3612−0097 1M CF24 1500 60 851VU 1HA1−AB 12A E0170FA2200 (a) A

11 851VU 2901VT 54R EN3155−016M2222 3612−0111 1M CF24 1500 60 851VU 1HA1−AA 11D E0170FA2200 (a) A

12 851VU 2901VT 54T EN3155−016M2222 3612−0112 1M CF24 3000 120 851VU 1HA2−AB 12A E0170FA2200 (a) A

13 851VU 1HA1−AB 11A E0170FA2200 3612−0110 1M CF24 2500 100 851VU 2947VG GND EN3155−015F2018 (a) A

14 851VU 1HA2−AB 11A E0170FA2200 3612−0113 1M CF24 3000 120 851VU 2947VG GND EN3155−015F2018 (a) A

15 851VU 2901VT 54Y EN3155−016M2222 3612−0072 1M CF24 2500 100 801VU 2615VC 19 EN3155−014M2018 (a) A

16 851VU 2901VT 54U EN3155−016M2222 3612−0098 1M CF24 3000 120 852VU 1HA3−AB 12A E0170FA2200 (a) A

17 851VU 2901VT 54V EN3155−016M2222 3612−0099 1M CF24 3500 140 852VU 1HA4−AB 12A E0170FA2200 (a) A

18 851VU 1HA1−AA 7B E0170FA2200 3622−0538 2S CF24 6000 240 804VU 2712VC 55 EN3155−008M2222 (a) A

19 851VU 1HA1−AA 8B E0170FA2200 3622−0539 2S CF24 6000 240 804VU 2712VC 72 EN3155−008M2222 (a) A

20

21

22

23

24

25

 (a) = BUNDLE F9000095227895 GND = GROUND

 A = ADDED WIRE

 D = DELETED WIRE

Figure A-FCAAA - Sheet 04

Modification of the Wiring in the Main Rack 800VU

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 617

6

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@A340

SERVICE BULLETIN

**CONF ALL

Figure A-FCBAA - Sheet 01

Modification of the Wiring between the Cargo Compartment and the Avionics Compartment

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 618

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF ALL

END1 LEAD END2

Instructions Zone or

Panel Elec.Ident. Term Terminal P/N

Wire

Ident. Co Rte Gauge

Lenght

mm Inch

Zone or

Panel Elec.Ident. Term Terminal P/N

L

i

n

e

 1 132 3506VC−A 69 EN3155−003F2222 3622−0542 2S CF24 35000 1400 152 3672VC−A 37 EN3155−003F2222 (a) A

 2

 3

 4

 5

 6

 7

 8

 9

10

11

12

13

14

15

16

17

18

19

20

21

22

23

24

25

 (a) = BUNDLE F9000095227895

 A = ADDED WIRE

Figure A-FCBAA - Sheet 02

Modification of the Wiring between the Cargo Compartment and the Avionics Compartment

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 619

6

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@A340

SERVICE BULLETIN

**CONF ALL

Figure A-FCCAA - Sheet 01

Installation of the Wiring of the New Sensing Elements

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 620

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF ALL

END1 LEAD END2

Instructions Zone or

Panel Elec.Ident. Term Terminal P/N

Wire

Ident. Co Rte Gauge

Lenght

mm Inch

Zone or

Panel Elec.Ident. Term Terminal P/N

L

i

n

e

 1 132 3520VC−A 66 EN3155−003F2222 3622−0540 2S DK22 25000 1000 137 3520VP / (a) A

 2 137 3520VP / 193 3591VS A NSA936809RG0002 (a) A

 3

 4

 5

 6

 7

 8

 9

10

11

12

13

14

15

16

17

18

19

20

21

22

23

24

25

 (a) = BUNDLE F9000095227895

 A = ADDED WIRE

Figure A-FCCAA - Sheet 02

Installation of the Wiring of the New Sensing Elements

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 621

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF ALL

ELAPSED TIME ASSUMPTIONS SERVICE BULLETIN No. A340−36−4033

SB ELAPSED TIME

(HOURS)

GET ACCESS

MH ET/S

TOTAL MANHOURS

SB ELAPSED TIME

184.00

90.00

STEPS

20.00 5.00

0 5 10 15 20 25 30 90

TESTS 4.00 4.00

CLOSE−UP 28.00 7.00

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.

MANHOURS GIVEN IN VENDOR SERVICE BULLETINS ARE NOT REFLECTED IN THIS GANTT CHART.

01

02

NOTES:

PER

4

1

4

:

:

85

REMOVAL OF SENSING ELEMENTS FR39−FR44 4.00 4.00 1

35 40 45 50 55 60 65 70 75 80

REMOVAL OF SENSING ELEMENTS FR44−FR51 4.00 4.00 1

REMOVAL OF SENSING ELEMENTS FR51−FR53.6 4.00 4.00 1

REMOVAL OF SENSING ELEMENTS FR53.6−FR55 4.00 4.00 1

REMOVAL OF DUCTS FR53.5−FR53.6 1.00 1.00 1

DRILLING OF NEW HOLE FR53.5−FR53.6 1.00 1.00 1

INSTALLATION OF SUPPORT FR53.5−FR53.6 1.00 1.00 1

INSTALLATION OF DUCTS FR53.5−FR53.6 2.00 2.00 1

REMOVAL OF DUCTS FR43−FR45 1.00 1.00 1

REPLACEMENT OF WEB ASSY FR44 3.00 3.00 1

INSTALLATION OF BRACKET FR44 1.00 1.00 1

INSTALLATION OF DUCTS FR43−FR45 2.00 2.00 1

INSTALLATION OF SENSING ELEMENTS FR39−FR44 14.00 14.00 1

INSTALLATION OF SENSING ELEMENTS FR44−FR50 14.00 14.00 1

INSTALLATION OF SENSING ELEMENTS FR50−FR53.6 21.00 21.00 1

INSTALLATION OF SENSING ELEMENTS FR53.6−FR55 14.00 14.00 1

REMOVAL OF DUCTS FR39−FR40 1.00 1.00 1

INSTALLATION OF SUPPORT FR39.1−FR39.2 3.00 3.00 1

INSTALLATION OF INTERCONNECTING ELECTRICAL WIRE 3.00 3.00 1

INSTALLATION OF NEW HARNESS 2SG 26.00 13.00 2

INSTALLATION OF THE WIRING 2.00 2.00 1

MODIFICATION OF THE WIRING IN 800VU 4.00 2.00 2

INSTALLATION OF DUCTS FR39−FR40 2.00 2.00 1

F_SB_364033_5_AAAA_01_01

Figure A-FAAAA - Sheet 01

Gantt Chart

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 622

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 001, 003 thru 004

TYPICAL PLACARD

INSTALLATION

AD

TYPICAL

5704VB /2S

FR18

FR19

FR37.1

FR38

B

B

C

FR26

FR29

C

SB 36−4033

2712VCA /2S

3520VC /2S

3506VC /2S

A

A

Z130

NOTE:

01 TIED TOGETHER WITH ITEMS, 404, 405 OR 406

01

TO EXISTING CABLE HARNESS F_SB_364033_6_BAAA_01_00

400

404

405

406

402

405

406

407

Figure A-GBAAA - Sheet 01

Installation of the Electrical Wiring in the FWD Cargo Compartment

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 623

6

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@A340

SERVICE BULLETIN

**CONF 005

TYPICAL PLACARD

INSTALLATION

TYPICAL

B

C

SB 36−4033

A

Z130

NOTE:

01 TIED TOGETHER WITH ITEMS, 404, 405 OR 406

TO EXISTING CABLE HARNESS

5704VB /2S

FR18

FR19

FR37.1

FR38

FR26.1

FR26.2

B

C

AD

2712VCA /2S

3520VC /2S

3506VC /2S

A

405

406

407

404

405

406

402

F_SB_364033_6_BAAE_01_00

01 401

Figure A-GBAAE - Sheet 01

Installation of the Electrical Wiring in the FWD Cargo Compartment

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 624

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 002

TYPICAL PLACARD

INSTALLATION

TYPICAL

B

C

SB 36−4033

A

Z130

NOTE:

01 TIED TOGETHER WITH ITEMS, 404, 405 OR 406

TO EXISTING CABLE HARNESS

5704VB /2S

FR18

FR19

FR37.1

FR38

FR26.1

FR26.2

B

C

AD

2712VCA /2S

3520VC /2S

3506VC /2S

A

F_SB_364033_6_BAAB_01_00

400

405

406

407

404

405

406

402

01

Figure A-GBAAB - Sheet 01

Installation of the Electrical Wiring in the FWD Cargo Compartment

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 625

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 001 thru 004

NOTE:

01 TIED TOGETHER WITH ITEMS, 404, 405 OR 406

TO EXISTING CABLE HARNESS

TYPICAL PLACARD

INSTALLATION TYPICAL

B

FR80

FR55 FR54

AD

5866VB /2S

D E

C

B

3672VC /2S A

5208VP

5866VB /2S

Z170

Z160

Z150

A

01

SB 36−4033

F_SB_364033_6_BBAA_01_00

C

400

404

405

406

402

405

406

407

/82

Figure A-GBBAA - Sheet 01

Installation of the Electrical Wiring in the AFT Cargo Compartment

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 626

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 001 thru 004

5866VB /2S

FR80

E

5866VB /2SF

FR80

5866VB /2S

5866VB /2SF

ALTERNATIVE

D

F_SB_364033_6_BBAA_02_00

(403)

(403)

/82

/82

Figure A-GBBAA - Sheet 02

Installation of the Electrical Wiring in the AFT Cargo Compartment

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 627

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 005

F_SB_364033_6_BBAE_01_00

NOTE:

01 TIED TOGETHER WITH ITEMS, 404, 405 OR 406

TO EXISTING CABLE HARNESS

TYPICAL PLACARD

INSTALLATION TYPICAL

B

FR80

FR55 FR54

AD

5866VB /2S

D E

C

B

3672VC /2S A

5208VP

5866VB /2S

Z170

Z160

Z150

A

01

SB 36−4033

C

401

405

406

407

404

405

406

402

/82

Figure A-GBBAE - Sheet 01

Installation of the Electrical Wiring in the AFT Cargo Compartment

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 628

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 005

F_SB_364033_6_BBAE_02_00

5866VB /2S

FR80

E

5866VB /2SF

FR80

5866VB /2S

5866VB /2SF

ALTERNATIVE

D

(403)

(403)

/82

/82

Figure A-GBBAE - Sheet 02

Installation of the Electrical Wiring in the AFT Cargo Compartment

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 629

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 001 thru 004

FR80/82

FR83

FR84

FR90

FR91

FR93

5866VB /2S

B C

F

X

Z310

A

F_SB_364033_6_BCAA_01_00

5208VP

5151VS

5215VC

A

Figure A-GBCAA - Sheet 01

Preparation for the Electrical Wiring Installation in the Rear Fuselage Section

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 630

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 001 thru 004

VIEW LOOKING AFT

VIEW LOOKING AFT

ALTERNATIVE

5208VP

5208VP

5866VB /2S

FR80 5866VB /2S

FR80/82

/82

B

C

D

E

F_SB_364033_6_BCAA_02_00

Figure A-GBCAA - Sheet 02

Preparation for the Electrical Wiring Installation in the Rear Fuselage Section

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 631

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 001 thru 004

(4 POS)

(8 POS)

(8 POS)

(4 POS)

(4 POS)

(4 POS)

D

(4 POS)

(6 POS)

(6 POS)

(4 POS)

(4 POS)

(4 POS)

E

ALTERNATIVE

(2 POS)

(2 POS)

F_SB_364033_6_BCAA_03_00

(416)

(417)

(418)

(417)

(419)

(415)

(420)

(410)

(411)

(410)

(411)

(416)

(417)

(418)

(417)

(419)

(415)

(417)

(423)

(420)

Figure A-GBCAA - Sheet 03

Preparation for the Electrical Wiring Installation in the Rear Fuselage Section

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 632

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 001 thru 004

VIEW LOOKING UP

FWD

FR90 FR91

STGR6LH

STGR10LH

STGR6RH

STGR10RH

AD

G

L M

N

P

T

T

U

V

W

F

F_SB_364033_6_BCAA_04_00

(450)

Figure A-GBCAA - Sheet 04

Preparation for the Electrical Wiring Installation in the Rear Fuselage Section

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 633

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 001 thru 004

G

VIEW LOOKING AFT

5866VB /2S

H

J

K

J

5215VC

(4 POS)

(4 POS)

(4 POS)

H

K

F_SB_364033_6_BCAA_05_00

(353)

(417)

(314)

(419)

(417)

(314)

(432)

(431)

(430)

(437)

(437)

(437)

(435)

Figure A-GBCAA - Sheet 05

Preparation for the Electrical Wiring Installation in the Rear Fuselage Section

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 634

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 001 thru 004

M

N

NOTE:

01 IF INSTALLED

01

01

F_SB_364033_6_BCAA_06_00

L

(442)

(437)

(437)

(437)

(437)

(437)

(437)

(417)

(444)

(417)

(444)

(419)

(417)

(314)

Figure A-GBCAA - Sheet 06

Preparation for the Electrical Wiring Installation in the Rear Fuselage Section

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 635

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 001 thru 004

P

FR91

FR90

5866VB /2S

Q R

S

Q

R

S

ALTERNATIVE

F_SB_364033_6_BCAA_07_00

(437)

(437)

(437)

(437)

(437)

(437)

(442)

(437) (442)

(417)

(314)

(448)

(417)

(501)

(439)

(419)

(417)

(444)

Figure A-GBCAA - Sheet 07

Preparation for the Electrical Wiring Installation in the Rear Fuselage Section

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 636

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 001 thru 004

TYPICAL

T U

W

V

F_SB_364033_6_BCAA_08_00

(437)

(437)

(437)

(437)

(437)

(437)

(437)

(443)

(417)

(314)

(314)

(417)

(417)

(314)

(442)

(417)

(444)

(417)

(314)

Figure A-GBCAA - Sheet 08

Preparation for the Electrical Wiring Installation in the Rear Fuselage Section

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 637

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 001 thru 004

FR93

STGR5RH

STGR6RH

STGR7RH

STGR9RH

5865VB /1S

FR91 FR92 FR93

STGR5RH

5856VB /1S

STGR10RH

VIEW LOOKING FWD

TYPICAL

X Y

Y

Z

Z

Z

A A

A B

F_SB_364033_6_BCAA_09_00

(479)

(480)

(481)

(448)

(417)

(501)

(442)

(437)

5151VS

5865VB /1S

Figure A-GBCAA - Sheet 09

Preparation for the Electrical Wiring Installation in the Rear Fuselage Section

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 638

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 001 thru 004

A A

A B

F_SB_364033_6_BCAA_10_00

(437)

(437)

(437)

(437) (464)

(417)

(470)

(449)

(471)

(419)

(465)

Figure A-GBCAA - Sheet 10

Preparation for the Electrical Wiring Installation in the Rear Fuselage Section

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 639

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 005

Z310

A

F_SB_364033_6_BCAE_01_00

FR80/82

FR83

FR84

FR90

FR91

FR93

5866VB /2S

B

D

V

5208VP

5151VS

5215VC

A

Figure A-GBCAE - Sheet 01

Preparation for the Electrical Wiring Installation in the Rear Fuselage Section

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 640

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 005

F_SB_364033_6_BCAE_02_00

VIEW LOOKING AFT

5208VP

5866VB /2S

FR80/82

C

(4 POS)

(6 POS)

(6 POS)

(4 POS)

(4 POS)

(4 POS)

(2 POS)

(2 POS)

(2 POS)

(2 POS)

(6 POS)

(6 POS)

C

B

(417)

(417)

(426)

(418)

(417)

(419)

(415)

(419)

(417)

(417)

(427)

(420)

(412)

(412)

(419)

Figure A-GBCAE - Sheet 02

Preparation for the Electrical Wiring Installation in the Rear Fuselage Section

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 641

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 005

F_SB_364033_6_BCAE_03_00

VIEW LOOKING UP

FWD

FR90 FR91

STGR6LH

STGR10LH

STGR6RH

STGR10RH

AD

J K

L

M

R

R

S

T

U

D

(502)

E

Figure A-GBCAE - Sheet 03

Preparation for the Electrical Wiring Installation in the Rear Fuselage Section

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 642

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 005

F_SB_364033_6_BCAE_04_00

VIEW LOOKING AFT

5866VB /2S

5215VC

(4 POS)

(4 POS)

(4 POS)

E

F

F

G

G

H

H

(353)

(417)

(314)

(417)

(314) (419)

(432)

(431)

(430)

(437)

(437)

(433)

(437)

Figure A-GBCAE - Sheet 04

Preparation for the Electrical Wiring Installation in the Rear Fuselage Section

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 643

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 005

F_SB_364033_6_BCAE_05_00

NOTE:

01 IF INSTALLED

01

01 K

L

J

(417)

(444)

(417)

(314)

(419)

(417)

(314)

(437)

(442)

(437)

(437)

(437)

(437)

(437)

Figure A-GBCAE - Sheet 05

Preparation for the Electrical Wiring Installation in the Rear Fuselage Section

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 644

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 005

F_SB_364033_6_BCAE_06_00

FR91

FR90

5866VB /2S

ALTERNATIVE

M

N

Q

N P

Q

P

(448)

(417)

(314)

(417)

(501)

(439)

(419)

(417)

(444)

(437)

(437)

(437)

(442)

(437)

(437)

(437)

(442)

(437)

Figure A-GBCAE - Sheet 06

Preparation for the Electrical Wiring Installation in the Rear Fuselage Section

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 645

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 005

F_SB_364033_6_BCAE_07_00

TYPICAL

R S

U

T

(417)

(314)

(417)

(314)

(443)

(417)

(314)

(417)

(314) (417)

(444)

(437)

(437)

(437)

(437)

(437)

(442)

(437)

(437)

Figure A-GBCAE - Sheet 07

Preparation for the Electrical Wiring Installation in the Rear Fuselage Section

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 646

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 005

F_SB_364033_6_BCAE_08_00

FR93

STGR5RH

STGR6RH

STGR7RH

STGR9RH

5865VB /1S

FR91 FR92 FR93

STGR5RH

5856VB /1S

STGR10RH

VIEW LOOKING FWD

TYPICAL

V W

W

X

X

X

Y

Z

(479)

(480)

(481)

(439)

(417)

(501)

(442)

(437)

5151VS

5865VB /1S

Figure A-GBCAE - Sheet 08

Preparation for the Electrical Wiring Installation in the Rear Fuselage Section

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 647

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 005

F_SB_364033_6_BCAE_09_00

Y

Z

(470)

(464)

(470)

(465)

(471)

(437)

(437)

(437)

(436) (437)

(471)

Figure A-GBCAE - Sheet 09

Preparation for the Electrical Wiring Installation in the Rear Fuselage Section

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 648

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 001 thru 004

Z310

A

FR80/82

FR83

FR84

FR90

FR91

FR93

5866VB /2S

B

B

TYPICAL PLACARD

INSTALLATION

C D

G

A

A A

SB 36−4033

F_SB_364033_6_BDAA_01_00

404

405

406

402

400

5208VP

5151VS

5215VC

5410VS

5866VB /2S

Figure A-GBDAA - Sheet 01

Installation of the Electrical Wiring in the Rear Fuselage Section

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 649

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 001 thru 004

VIEW LOOKING AFT

VIEW LOOKING AFT

ALTERNATIVE

5208VP

5208VP

5866VB /2S

FR80 5866VB /2S

FR80/82

/82

C

D

E

F

F_SB_364033_6_BDAA_02_00

Figure A-GBDAA - Sheet 02

Installation of the Electrical Wiring in the Rear Fuselage Section

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 650

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 001 thru 004

(4 POS)

(8 POS)

(8 POS)

(4 POS)

(4 POS)

(4 POS)

(4 POS)

(6 POS)

(6 POS)

(4 POS)

(4 POS)

(4 POS)

ALTERNATIVE

(2 POS)

(2 POS)

E

F

(3 POS)

(3 POS)

F_SB_364033_6_BDAA_03_00

416

420

417

418

417

419

415

415

485

416

417

418

417

419

415

485

415

417

423

420

(411)

(410)

(411)

(410)

Figure A-GBDAA - Sheet 03

Installation of the Electrical Wiring in the Rear Fuselage Section

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 651

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 001 thru 004

VIEW LOOKING UP

FWD

FR90 FR91

STGR6LH

STGR10LH

STGR6RH

STGR10RH

AD

H

M N

P

Q

U

U

V

W

X

Y

Z

FR93

G

F_SB_364033_6_BDAA_04_00

402

510

511

402

488

489

402

451

Figure A-GBDAA - Sheet 04

Installation of the Electrical Wiring in the Rear Fuselage Section

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 652

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 001 thru 004

VIEW LOOKING AFT

5866VB /2S

5215VC

(4 POS)

(4 POS)

(4 POS)

H

J

J

K

K

L

L

5215VC

F_SB_364033_6_BDAA_05_00

353

(437)

417

314

(437)

419

(437)

417

314

432

431

430

(435)

Figure A-GBDAA - Sheet 05

Installation of the Electrical Wiring in the Rear Fuselage Section

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 653

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 001 thru 004

NOTE:

01 IF INSTALLED

01

01

M

N

P

F_SB_364033_6_BDAA_06_00

(442)

(437)

(437)

(437)

(437)

350

417

444

350

417

314

419

417

314

Figure A-GBDAA - Sheet 06

Installation of the Electrical Wiring in the Rear Fuselage Section

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 654

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 001 thru 004

FR91

FR90

5866VB /2S

ALTERNATIVE

Q

R

R S

T

T

F_SB_364033_6_BDAA_07_00

S

437

(437)

417

314

448

(437)

(437)

(442)

(437)

417

501

439

444

417

350

(437) 419

(442)

Figure A-GBDAA - Sheet 07

Installation of the Electrical Wiring in the Rear Fuselage Section

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 655

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 001 thru 004

TYPICAL

U

V

5215VC

5410VC

5866VB /2S

TO

TO

W

(437) (437)

(437)

350

417

314

320

417

501

496

492

496

419

494

493

402

488

402

510

493

494

402 351

451

489

511

5866VB /2S

F_SB_364033_6_BDAA_08_01

843

469

Figure A-GBDAA - Sheet 08

Installation of the Electrical Wiring in the Rear Fuselage Section

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 656

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 001 thru 004

X

Z

Y

(442)

(437)

(437)

350

417

444

419

515

417

314

511

517

404

510

F_SB_364033_6_BDAA_09_01

518

Figure A-GBDAA - Sheet 09

Installation of the Electrical Wiring in the Rear Fuselage Section

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 657

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 001 thru 004

STGR5RH

STGR6RH

STGR7RH

STGR9RH

5865VB /1S

FR91 FR92 FR93

STGR5RH

STGR10RH

VIEW LOOKING FWD

TYPICAL

BONDING STRIP ATTACHED TO INSIDE OF CLAMP

A B 5866VB /2S

A B

A C

A C

A D

A D

A E

5410VS

5151VS

NOTE:

02

5866VB /2S

A F

A D

F_SB_364033_6_BDAA_10_00

479

480

481

479

480

481

(442) (437)

528

471

320

352

472

515

469

470

476

536

471

320

475

FR93

A A

02

02

5866VB /2S

TO 361HF

5865VB /1S

TO 34HF

Figure A-GBDAA - Sheet 10

Installation of the Electrical Wiring in the Rear Fuselage Section

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 658

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 001 thru 004

A F

F_SB_364033_6_BDAA_11_00

(437)

(437)

(437)

(437) (442)

470

470

449

471

449

471

536

537

465

417

521

419

A E

Figure A-GBDAA - Sheet 11

Installation of the Electrical Wiring in the Rear Fuselage Section

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 659

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 005

Z310

A

FR80/82

FR83

FR84

FR90

FR91

FR93

5866VB /2S

B

B

TYPICAL PLACARD

INSTALLATION

C D

G

A

A A

SB 36−4033

F_SB_364033_6_BDAE_01_00

404

405

406

402

401

5208VP

5151VS

5215VC

5410VS

5866VB /2S

Figure A-GBDAE - Sheet 01

Installation of the Electrical Wiring in the Rear Fuselage Section

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 660

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 005

F_SB_364033_6_BDAE_02_00

VIEW LOOKING AFT

5208VP

5866VB /2S

FR80/82

(4 POS)

(6 POS)

(6 POS)

(4 POS)

(4 POS)

(4 POS)

(2 POS)

(2 POS)

(2 POS)

(2 POS)

(6 POS)

(6 POS)

(3 POS)

D

D

C

417

417

426

420

427

417

417

419

415

485

415

419

417

418

419

(412)

(412)

Figure A-GBDAE - Sheet 02

Installation of the Electrical Wiring in the Rear Fuselage Section

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 661

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 005

F_SB_364033_6_BDAE_03_00 VIEW LOOKING UP

FWD

FR90 FR91

STGR6LH

STGR10LH

STGR6RH

STGR10RH

AD

FR93

F

K L

M

N

S

S

T

U

V

W

X

E

451

511

5866VB /2S

402

488

489

402

510

402

Figure A-GBDAE - Sheet 03

Installation of the Electrical Wiring in the Rear Fuselage Section

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 662

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 005

F_SB_364033_6_BDAE_04_00

VIEW LOOKING AFT

5866VB /2S

5215VC

(4 POS)

(4 POS)

(4 POS)

5215VC

F

G

G

H

H

J

J

353

417

314

432

431

430

(433)

314

417

419

(437)

(437)

(437)

Figure A-GBDAE - Sheet 04

Installation of the Electrical Wiring in the Rear Fuselage Section

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 663

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 005

F_SB_364033_6_BDAE_05_00

NOTE:

01 IF INSTALLED

01

01

K

L

M

350

417

444

350

417

314

419

314

417

(442)

(437)

(437)

(437)

(437)

Figure A-GBDAE - Sheet 05

Installation of the Electrical Wiring in the Rear Fuselage Section

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 664

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 005

F_SB_364033_6_BDAE_06_00

FR91

FR90

5866VB /2S

ALTERNATIVE

N

P

P Q

R

R

Q

448

417

314

417

501

439

419

350

417

444

(437)

(437)

(437)

(437)

(442)

(437)

(437) (442)

Figure A-GBDAE - Sheet 06

Installation of the Electrical Wiring in the Rear Fuselage Section

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 665

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 005

TYPICAL

S

T

5215VC

5410VC

5866VB /2S

TO

TO

U

350

417

314

320

417

501

419

496

492

496

494

493

402

489

401

402

493

494

402 351

451

511

(437) (437)

(437)

5866VB /2S

488

F_SB_364033_6_BDAE_07_01

843

469

Figure A-GBDAE - Sheet 07

Installation of the Electrical Wiring in the Rear Fuselage Section

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 666

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 005

V

W

X

350

417

444

419

515

417

314

404

517

511

(442)

(437)

(437)

518

F_SB_364033_6_BDAE_08_01

510

Figure A-GBDAE - Sheet 08

Installation of the Electrical Wiring in the Rear Fuselage Section

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 667

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 005

F_SB_364033_6_BDAE_09_00

STGR5RH

STGR7RH

STGR9RH

5865VB /1S

FR91 FR92 FR93

STGR5RH

STGR10RH

VIEW LOOKING FWD

TYPICAL

BONDING STRIP ATTACHED TO INSIDE OF CLAMP

5866VB /2S

NOTE:

02

5866VB /2S

Z

Z

A A

A B

A B

A B

A C

A D

A A

479

480

481

479

480

481

528

471

352

472 320

469

515

470

476

320

536

471

475

(442) (437)

FR93

Y

02

02

STGR6RH

5410VS

5151VS

5866VB /2S

TO 361HF

5865VB /1S

TO 34HF

Figure A-GBDAE - Sheet 09

Installation of the Electrical Wiring in the Rear Fuselage Section

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 668

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 005

F_SB_364033_6_BDAE_10_00

A D

(437)

(437)

(437)

(442) (437)

470

470

471

536 449

471

449

537

419

521

417

465

A C

Figure A-GBDAE - Sheet 10

Installation of the Electrical Wiring in the Rear Fuselage Section

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 669

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF ALL

A

B

C

mm

DIMENSIONS

(in)

C

B

A DIA 5.1

22.0

25.0

DIA 0.20

0.87

0.98

FR89

FR90

FR91

FR91

STGR6RH

STGR6RH

B

01

FWD

B

Z310

A

F_SB_364033_6_BEAA_01_00

A

460

462

314

463

461 460

STGR6RH

C

C

INSTALL WITH CORROSION INHIBITIVE

INTERFAY SEALANT (MAT. NO. 09−005)

01

NOTE:

Figure A-GBEAA - Sheet 01

Installation of the Bracket between FR90 and FR91

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 670

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 001, 003

FR55

FR57

FR60

FR64

FR68

FR73

FR77

C

B

D

D

E

D

C

32HF

31HF

30HF

29HF

28HF

27HF

A

E

B

E

E

E

D

E

E

FR83

F

F_SB_364033_6_BFAA_01_00

(572)

(570)

(563)

(566)

(564)

(562)

A

Z310

Z170

Z160 Z150

Figure A-GBFAA - Sheet 01

Removal of the Sensing Elements in the Bulk and AFT Cargo Compartments

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 671

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 001, 003

TYPICAL

01

NOTE:

01

B

REMOVE RIVETS

TYPICAL

C

F_SB_364033_6_BFAA_02_00

(602)

(357)

(408)

(408)

(602)

(357)

(609)

(609)

(592)

(612)

Figure A-GBFAA - Sheet 02

Removal of the Sensing Elements in the Bulk and AFT Cargo Compartments

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 672

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 001, 003

TYPICAL

01

NOTE:

REMOVE RIVETS

TYPICAL

01

E

D

02

02 NUT, PART OF ITEM (355)

F

F_SB_364033_6_BFAA_03_00

(408)

(399)

(601)

(357)

(602)

(357)

(602)

(596)

(355)

(596)

(609)

(592)

(612)

Figure A-GBFAA - Sheet 03

Removal of the Sensing Elements in the Bulk and AFT Cargo Compartments

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 673

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 002, 004

FR57

FR57.4

FR60

FR64

FR68

FR73

FR77

FR83

FR55

26HF

B

D

D

E

D

C

32HF

31HF

30HF

29HF

28HF

27HF

E

E

E

E

D

E

E

F

B

A

C

B

C

F_SB_364033_6_BFAB_01_00

(572)

(570)

(563)

(566)

(564)

(562)

(358)

A

Z310

Z170

Z160 Z150

Figure A-GBFAB - Sheet 01

Removal of the Sensing Elements in the Bulk and AFT Cargo Compartments

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 674

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 002, 004

TYPICAL

01

NOTE:

01

B

REMOVE RIVETS

TYPICAL

C

F_SB_364033_6_BFAB_02_00

(599)

(592)

(602)

(357)

(602)

(357)

(609)

(609)

(620)

(620)

Figure A-GBFAB - Sheet 02

Removal of the Sensing Elements in the Bulk and AFT Cargo Compartments

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 675

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 002, 004

TYPICAL

01

NOTE:

REMOVE RIVETS

TYPICAL

01

E

D

02

02 NUT, PART OF ITEM (355)

F

F_SB_364033_6_BFAB_03_00

(609)

(620)

(399)

(601) (596)

(599) (592)

(357)

(602)

(357)

(602)

(597)

(355)

Figure A-GBFAB - Sheet 03

Removal of the Sensing Elements in the Bulk and AFT Cargo Compartments

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 676

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 005

F_SB_364033_6_BFAE_01_00

FR57

FR57.4

FR60

FR64

FR68

FR73

FR77

FR83

FR55

26HF

B

D

D

E

D

C

32HF

31HF

30HF

29HF

28HF

27HF

E

E

E

E

D

E

E

F

B

A

C

B

C

A

Z310

Z170

Z160 Z150

(564)

(566)

(358)

(563)

(562)

(570)

(572)

Figure A-GBFAE - Sheet 01

Removal of the Sensing Elements in the Bulk and AFT Cargo Compartments

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 677

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 005

F_SB_364033_6_BFAE_02_00

TYPICAL

01

NOTE:

01

B

REMOVE RIVETS

TYPICAL

C

(592)

(602)

(357)

(602)

(357)

(599)

(609)

(408)

(408)

(609)

Figure A-GBFAE - Sheet 02

Removal of the Sensing Elements in the Bulk and AFT Cargo Compartments

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 678

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 005

F_SB_364033_6_BFAE_03_00

TYPICAL

TYPICAL

01

E

D

F

01

NOTE:

REMOVE RIVETS

(602)

(357)

(592)

(357)

(602)

(604)

(602)

(609)

(408)

(599)

(399)

(601)

Figure A-GBFAE - Sheet 03

Removal of the Sensing Elements in the Bulk and AFT Cargo Compartments

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 679

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 001, 003

FR57

FR57.4

FR60

FR64

FR68

FR73

FR77 FR83

FR55

B

27HF

352HF

351HF

26HF

32HF

31HF

30HF

29HF

28HF

353HF

354HF

355HF

356HF

357HF

C

D

E

F

G

H

J

K

A

574

572

570

570

563

563

566

566

564

564

562

562

358

358

A

Z310

Z170

Z160 Z150

F_SB_364033_6_BGAA_01_01

P

STANDARD

CLAMP

INSTALLATION

Q

NOTE:

THE SENSING ELEMENTS MUST BE INSTALLED IN FRONT OF THE VENTILATION HOLES.

THE LENGTH COMPENSATION OF THE SENSING ELEMENTS MUST BE DONE AT

THE COUPLINGS OR RETAINER RINGS.

Figure A-GBGAA - Sheet 01

Installation of the Sensing Elements in the Bulk and AFT Cargo Compartments

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 680

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 001, 003

FR56 FR55

FR57

C

K

352HF 312HF

FWD

B

M M

FWD

593

01

NOTE:

BOND WITH ADHESIVE (MAT. NO. 08−078) AND

PROTECT WITH VARNISH (MAT. NO. 07−003C)

01 606 01

F_SB_364033_6_BGAA_02_02

Figure A-GBGAA - Sheet 02

Installation of the Sensing Elements in the Bulk and AFT Cargo Compartments

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 681

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 001, 003

FR60

FR64

FWD

FWD

M K

M K

352HF

353HF

E

D

356

01

NOTE:

BOND WITH ADHESIVE (MAT. NO. 08−078) AND

PROTECT WITH VARNISH (MAT. NO. 07−003C)

01

01 606

F_SB_364033_6_BGAA_03_02

Figure A-GBGAA - Sheet 03

Installation of the Sensing Elements in the Bulk and AFT Cargo Compartments

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 682

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 001, 003

FR68

FR73

F

FWD

FWD

M

355HF 354HF

355HF

M K

G

594 591

594

01

NOTE:

BOND WITH ADHESIVE (MAT. NO. 08−078) AND

PROTECT WITH VARNISH (MAT. NO. 07−003C)

01 01

01

F_SB_364033_6_BGAA_04_01

K

Figure A-GBGAA - Sheet 04

Installation of the Sensing Elements in the Bulk and AFT Cargo Compartments

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 683

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 001, 003

FR77

FR80

FWD

FWD

356HF

K

H

J

01

NOTE:

BOND WITH ADHESIVE (MAT. NO. 08−078) AND

PROTECT WITH VARNISH (MAT. NO. 07−003C)

01 611

F_SB_364033_6_BGAA_05_02

N

Figure A-GBGAA - Sheet 05

Installation of the Sensing Elements in the Bulk and AFT Cargo Compartments

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 684

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 001, 003

M

TYPICAL

607

612

607

(408)

602

357

602

(612)

592

609

02 SECURE WITH LOCKWIRE (MAT. NO. 19−018)

NOTE:

03

03

03

F_SB_364033_6_BGAA_06_01

03 TORQUE VALUE 0.25m.daN (22lbf.in)

L

4.8 mm TO 7.9 mm

(0.19 in TO 0.31 in)

9.5 mm TO 12.7 mm

(0.37 in TO 0.50 in)

04

04

592

04 INSTALL THE BRACKET WITHIN THE GIVEN TOLERANCE AREA

TYPICAL

K

02

02

02

L

02

Figure A-GBGAA - Sheet 06

Installation of the Sensing Elements in the Bulk and AFT Cargo Compartments

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 685

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 001, 003

(399)

609 602

805

610

610 602 03

F_SB_364033_6_BGAA_07_02

03 TORQUE VALUE 0.25m.daN (22lbf.in)

NOTE:

TYPICAL

05

FR55 TO FR83

05 STANDARD CLAMP INSTALLATION FOR REMAINING AREAS.

FOR ALL OTHER CLAMP INSTALLATIONS REFER TO THE 

RELATED DETAILS.

N

P

357

602

602

03 (601)

(399)

Figure A-GBGAA - Sheet 07

Installation of the Sensing Elements in the Bulk and AFT Cargo Compartments

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 686

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 001, 003

375HF

OVERHEAT SENSING

ELEMENT 357HF

355

57

604

02

02

02

03

597

596

01

01 BOND WITH ADHESIVE (MAT. NO. 08−078) AND

02 SECURE WITH LOCKWIRE (MAT. NO. 19−018)

03 TORQUE VALUE 0.25m.daN (22lbf.in)

NUT, PART OF ITEM 355

NOTE:

PROTECT WITH VARNISH (MAT. NO. 07−003C)

F_SB_364033_6_BGAA_08_01

Q

06

06

Figure A-GBGAA - Sheet 08

Installation of the Sensing Elements in the Bulk and AFT Cargo Compartments

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 687

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 002, 004

FR57

FR57.4

FR60

FR64

FR68

FR73

FR77 FR83

FR55

B

27HF

352HF

351HF

26HF

32HF

31HF

30HF

29HF

28HF

353HF

354HF

355HF

356HF

357HF

C

D

E

F

G

H

J

K

A

574

572

570

570

563

563

566

566

564

564

562

562

358

358

A

Z310

Z170

Z160 Z150

F_SB_364033_6_BGAB_01_01

NOTE:

THE LENGTH COMPENSATION OF SENSING ELEMENTS MUST BE

DONE AT THE COUPLINGS OR RETAINER RINGS.

THE SENSING ELEMENTS MUST BE INSTALLED IN FRONT

OF THE VENTILATION HOLES.

STANDARD

CLAMP

INSTALLATION

Q

R

Figure A-GBGAB - Sheet 01

Installation of the Sensing Elements in the Bulk and AFT Cargo Compartments

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 688

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 002, 004

FR57

FR55

351HF 312HF

B

FWD

389 593

01

NOTE:

BOND WITH ADHESIVE (MAT. NO. 08−078) AND

PROTECT WITH VARNISH (MAT. NO. 07−003C)

01 01

F_SB_364033_6_BGAB_02_01

L

N N

Figure A-GBGAB - Sheet 02

Installation of the Sensing Elements in the Bulk and AFT Cargo Compartments

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 689

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 002, 004

352HF

FWD

FWD

C

D

FR57.3 FR57.2

FR57.4

606

01

NOTE:

BOND WITH ADHESIVE (MAT. NO. 08−078) AND

PROTECT WITH VARNISH (MAT. NO. 07−003C)

01

F_SB_364033_6_BGAB_03_01

L

N N

Figure A-GBGAB - Sheet 03

Installation of the Sensing Elements in the Bulk and AFT Cargo Compartments

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 690

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 002, 004

FR60

FR64

FWD

FWD

352HF

353HF

E

F

606

356

01

NOTE:

BOND WITH ADHESIVE (MAT. NO. 08−078) AND

PROTECT WITH VARNISH (MAT. NO. 07−003C)

01

01

F_SB_364033_6_BGAB_04_01

L

L

N

N

Figure A-GBGAB - Sheet 04

Installation of the Sensing Elements in the Bulk and AFT Cargo Compartments

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 691

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 002, 004

FR68

FR73

FWD

FWD

355HF 354HF

355HF

G

H

594 591

594

01

NOTE:

BOND WITH ADHESIVE (MAT. NO. 08−078) AND

PROTECT WITH VARNISH (MAT. NO. 07−003C)

01 01

01

F_SB_364033_6_BGAB_05_01

N

N

L

L

Figure A-GBGAB - Sheet 05

Installation of the Sensing Elements in the Bulk and AFT Cargo Compartments

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 692

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 002, 004

FR77

FR80

FWD

FWD

356HF

J

K

611

01

NOTE:

BOND WITH ADHESIVE (MAT. NO. 08−078) AND

PROTECT WITH VARNISH (MAT. NO. 07−003C)

01

/82

F_SB_364033_6_BGAB_06_01

L

P

Figure A-GBGAB - Sheet 06

Installation of the Sensing Elements in the Bulk and AFT Cargo Compartments

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 693

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 002, 004

TYPICAL

(609)

(620)

602

357

602

03

F_SB_364033_6_BGAB_07_01

607

612

607

599

592

03

03

4.8 mm TO 7.9 mm

(0.19 in TO 0.31 in)

9.5 mm TO 12.7 mm

(0.37 in TO 0.50 in)

04

04

592

TYPICAL

02

02

02

02

02 SECURE WITH LOCKWIRE (MAT. NO. 19−018)

NOTE:

03 TORQUE VALUE 0.25m.daN (22lbf.in)

04 INSTALL THE BRACKET WITHIN THE GIVEN TOLERANCE AREA

L

M

M

N

Figure A-GBGAB - Sheet 07

Installation of the Sensing Elements in the Bulk and AFT Cargo Compartments

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 694

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 002, 004

(399)

609 602

805

610

610 602

03 TORQUE VALUE 0.25m.daN (22lbf.in)

NOTE:

03

F_SB_364033_6_BGAB_08_01

P

TYPICAL

05

FR55 TO FR83

05 STANDARD CLAMP INSTALLATION FOR REMAINING AREAS.

FOR ALL OTHER CLAMP INSTALLATIONS REFER TO THE 

RELATED DETAILS.

357

03 (601)

(399)

Q

602

602

Figure A-GBGAB - Sheet 08

Installation of the Sensing Elements in the Bulk and AFT Cargo Compartments

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 695

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 002, 004

375HF

OVERHEAT SENSING

ELEMENT 357HF

355 597

57

604

596

02

02

02

03

01

01 BOND WITH ADHESIVE (MAT. NO. 08−078) AND

02 SECURE WITH LOCKWIRE (MAT. NO. 19−018)

03 TORQUE VALUE 0.25m.daN (22lbf.in)

06 NUT, PART OF ITEM 355

NOTE:

PROTECT WITH VARNISH (MAT. NO. 07−003C)

06

F_SB_364033_6_BGAB_09_01

R

Figure A-GBGAB - Sheet 09

Installation of the Sensing Elements in the Bulk and AFT Cargo Compartments

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 696

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 005

FR57

FR57.4

FR60

FR64

FR68

FR73

FR77 FR83

FR55

B

27HF

352HF

351HF

26HF

32HF

31HF

30HF

29HF

28HF

353HF

354HF

355HF

356HF

357HF

C

D

E

F

G

H

J

K

A

A

Z310

Z170

Z160 Z150

566

563

562

570

564

574

358

572

570

562

563

358

566

564

F_SB_364033_6_BGAE_01_01

NOTE:

THE LENGTH COMPENSATION OF SENSING ELEMENTS MUST BE

DONE AT THE COUPLINGS OR RETAINER RINGS.

THE SENSING ELEMENTS MUST BE INSTALLED IN FRONT

OF THE VENTILATION HOLES.

STANDARD

CLAMP

INSTALLATION

Q

R

Figure A-GBGAE - Sheet 01

Installation of the Sensing Elements in the Bulk and AFT Cargo Compartments

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 697

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 005

FR57

FR55

351HF 312HF

B

FWD

01

NOTE:

BOND WITH ADHESIVE (MAT. NO. 08−078) AND

PROTECT WITH VARNISH (MAT. NO. 07−003C)

01 389 01 593

F_SB_364033_6_BGAE_02_01

L

N N

Figure A-GBGAE - Sheet 02

Installation of the Sensing Elements in the Bulk and AFT Cargo Compartments

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 698

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 005

352HF

FWD

FWD

C

D

FR57.3 FR57.2

FR57.4

01

NOTE:

BOND WITH ADHESIVE (MAT. NO. 08−078) AND

PROTECT WITH VARNISH (MAT. NO. 07−003C)

01 606

F_SB_364033_6_BGAE_03_01

L

N N

Figure A-GBGAE - Sheet 03

Installation of the Sensing Elements in the Bulk and AFT Cargo Compartments

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 699

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 005

FR60

FR64

FWD

FWD

352HF

353HF

E

F

01

NOTE:

BOND WITH ADHESIVE (MAT. NO. 08−078) AND

PROTECT WITH VARNISH (MAT. NO. 07−003C)

01

01

356

606

F_SB_364033_6_BGAE_04_01

N

N

L

L

Figure A-GBGAE - Sheet 04

Installation of the Sensing Elements in the Bulk and AFT Cargo Compartments

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 700

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 005

FR68

FR73

FWD

FWD

355HF 354HF

355HF

G

H

01

NOTE:

BOND WITH ADHESIVE (MAT. NO. 08−078) AND

PROTECT WITH VARNISH (MAT. NO. 07−003C)

01 01

01

594 591

594

F_SB_364033_6_BGAE_05_01

L

N L

N

Figure A-GBGAE - Sheet 05

Installation of the Sensing Elements in the Bulk and AFT Cargo Compartments

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 701

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 005

FR77

FR80

FWD

FWD

356HF

J

K

01

NOTE:

BOND WITH ADHESIVE (MAT. NO. 08−078) AND

PROTECT WITH VARNISH (MAT. NO. 07−003C)

01 611

/82

F_SB_364033_6_BGAE_06_01

L

P

Figure A-GBGAE - Sheet 06

Installation of the Sensing Elements in the Bulk and AFT Cargo Compartments

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 702

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 005

TYPICAL

602

357

602

609

03 620

F_SB_364033_6_BGAE_07_01

607

612

607

592

02 SECURE WITH LOCKWIRE (MAT. NO. 19−018)

NOTE:

03

03

03 TORQUE VALUE 0.25m.daN (22lbf.in)

4.8 mm TO 7.9 mm

(0.19 in TO 0.31 in)

9.5 mm TO 12.7 mm

(0.37 in TO 0.50 in)

04

04

592

04 INSTALL THE BRACKET WITHIN THE GIVEN TOLERANCE AREA

TYPICAL

02

02

02

02

L

M

N

M

(599)

Figure A-GBGAE - Sheet 07

Installation of the Sensing Elements in the Bulk and AFT Cargo Compartments

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 703

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 005

609 602

805

610

610 602

(399)

03

F_SB_364033_6_BGAE_08_01

357

03 601

Q

P

03 TORQUE VALUE 0.25m.daN (22lbf.in)

NOTE:

TYPICAL

05

FR55 TO FR83

05 STANDARD CLAMP INSTALLATION FOR REMAINING AREAS.

FOR ALL OTHER CLAMP INSTALLATIONS REFER TO THE 

RELATED DETAILS.

602

602

399

Figure A-GBGAE - Sheet 08

Installation of the Sensing Elements in the Bulk and AFT Cargo Compartments

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 704

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 005

375HF

03

OVERHEAT SENSING

ELEMENT 357HF

02

02

02

604 596

57

597

355

01

06

F_SB_364033_6_BGAE_09_01

R

01 BOND WITH ADHESIVE (MAT. NO. 08−078) AND

02 SECURE WITH LOCKWIRE (MAT. NO. 19−018)

03 TORQUE VALUE 0.25m.daN (22lbf.in)

06 NUT, PART OF ITEM 355

NOTE:

PROTECT WITH VARNISH (MAT. NO. 07−003C)

Figure A-GBGAE - Sheet 09

Installation of the Sensing Elements in the Bulk and AFT Cargo Compartments

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 705

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 001 thru 002

Z310

A

A

FR80

FR83

FR85

FR86

FR88

FR91

FR93

FR95

FR98

FR100

C

B

34HF

33HF

139HF

140HF

C

C

C

C

E E

(364)

(366)

(371)

(361)

/82

F_SB_364033_6_BHAA_01_01

D

Figure A-GBHAA - Sheet 01

Removal of the Sensing Elements in the Rear Fuselage Section

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 706

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 001 thru 002

B

01

TYPICAL

NUT, PART OF ITEM (355)

TYPICAL

01

NOTE:

C

D

(596)

(357)

(357)

(620) (601)

(399)

(604)

(355)

(602) (602)

(609)

F_SB_364033_6_BHAA_02_01

FOR ALL CLAMPS

Figure A-GBHAA - Sheet 02

Removal of the Sensing Elements in the Rear Fuselage Section

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 707

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 001 thru 002

NOTE:

TYPICAL

02

02 REMOVE RIVETS

K

K

G

E

(59)

(612)

FWD

F

F_SB_364033_6_BHAA_03_01

J

H

C

Figure A-GBHAA - Sheet 03

Removal of the Sensing Elements in the Rear Fuselage Section

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 708

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 001 thru 002

TYPICAL

02

NOTE:

REMOVE RIVETS

02

G

H

J

(399)

(621)

(59)

(620)

(601)

(399)

(601)

(612)

(609)

(602)

(602)

(357)

(602)

F_SB_364033_6_BHAA_04_01

(621)

K

Figure A-GBHAA - Sheet 04

Removal of the Sensing Elements in the Rear Fuselage Section

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 709

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 003 thru 004

Z310

A

A

FR80

FR83

FR85

FR86

FR88

FR91

FR93

FR95

FR98

FR100

D

C

B

F

E

D

F

G

34HF

33HF

139HF

140HF

F_SB_364033_6_BHAC_01_00

(361)

(362)

(365)

(370)

/82

Figure A-GBHAC - Sheet 01

Removal of the Sensing Elements in the Rear Fuselage Section

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 710

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 003 thru 004

F_SB_364033_6_BHAC_02_00 NUT, PART OF ITEM (355)

TYPICAL

01

NOTE:

B

C

01

(604)

(596)

(355)

(602)

(603)

(610)

(609)

(602)

(620)

(610)

(609)

D

Figure A-GBHAC - Sheet 02

Removal of the Sensing Elements in the Rear Fuselage Section

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 711

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 003 thru 004

F_SB_364033_6_BHAC_03_00

TYPICAL

F

02

L K

K

J

H

D

(601)

(399)

(612)

(610)

(59)

(602)

NOTE:

02 REMOVE RIVETS

E

FWD

G

Figure A-GBHAC - Sheet 03

Removal of the Sensing Elements in the Rear Fuselage Section

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 712

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 003 thru 004

TYPICAL

02

NOTE:

REMOVE RIVETS

02

J

K

L

(612)

(609)

(399)

(621)

(59)

(357)

(620)

(602)

(399)

(357)

(601) (602)

(601)

H

F_SB_364033_6_BHAC_04_01

(602)

Figure A-GBHAC - Sheet 04

Removal of the Sensing Elements in the Rear Fuselage Section

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 713

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 005

Z310

A

F_SB_364033_6_BHAE_01_00

FR80

FR83

FR85

FR86

FR88

FR91

FR93

FR95

FR98

FR100

B

E

34HF

33HF

139HF

140HF

D

F

D

C

A

(361)

(368)

(362)

(365)

/82

Figure A-GBHAE - Sheet 01

Removal of the Sensing Elements in the Rear Fuselage Section

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 714

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 005

01 NUT, PART OF ITEM (355)

NOTE:

B

01

TYPICAL

TYPICAL

02

C

D

02 REMOVE RIVETS

(596)

(604)

(355)

(602)

(610)

(592)

(601)

(399)

(599)

F_SB_364033_6_BHAE_02_01

FOR ALL CLAMPS

Figure A-GBHAE - Sheet 02

Removal of the Sensing Elements in the Rear Fuselage Section

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 715

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 005

F_SB_364033_6_BHAE_03_00

E

G

H

J

K J

E

(602)

(610)

(620)

(609)

FWD

F

Figure A-GBHAE - Sheet 03

Removal of the Sensing Elements in the Rear Fuselage Section

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 716

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 005

TYPICAL

02

NOTE:

REMOVE RIVETS

02

G

H

J

K

(592)

(602)

(399)

(357)

(601) (602)

(601)

(602)

(599)

(609)

(399)

F_SB_364033_6_BHAE_04_01

(357)

(620)

(621)

Figure A-GBHAE - Sheet 04

Removal of the Sensing Elements in the Rear Fuselage Section

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 717

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 001 thru 002

Z310

A

MAKE SURE THAT THE SENSING ELEMENTS ARE INSTALLED IN FRONT

OF THE APU DUCT VENTILATION HOLES

01

NOTE:

FR80

FR83

FR85

FR86

FR88

FR91

FR93

FR95

FR98

FR100

B

C

D

L

33HF

358HF

139HF

359HF

140HF

360HF

34HF

361HF

361

360

366

366

364

364

371

398

/82

F_SB_364033_6_BJAA_01_01

A

01

STANDARD

CLAMP

INSTALLATION

R

E

F

F

F

G

H

K

Figure A-GBJAA - Sheet 01

Installation of the Sensing Elements in the Rear Fuselage Section

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 718

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 001 thru 002

FWD

D

D

OVERHEAT SENSING

ELEMENT 358HF

B

596

496

405

02

02

02

02

604

597

355

602

C

02

NOTE:

SECURE WITH LOCKWIRE (MAT. NO. 19−018)

03 NUT, PART OF ITEM 355

03

04 TORQUE VALUE 0.25m.daN (22lbf.in)

04

05 BOND WITH ADHESIVE (MAT. NO. 08−078) AND

PROTECT WITH VARNISH (MAT. NO. 07−003C)

05 608

F_SB_364033_6_BJAA_02_02

Figure A-GBJAA - Sheet 02

Installation of the Sensing Elements in the Rear Fuselage Section

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 719

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 001 thru 002

TYPICAL

D

(620)

(399)

805

(609)

357

602

602

609

602

610

610

NOTE:

04 TORQUE VALUE 0.25m.daN (22lbf.in)

04

04

F_SB_364033_6_BJAA_03_01

E

Figure A-GBJAA - Sheet 03

Installation of the Sensing Elements in the Rear Fuselage Section

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 720

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 001 thru 002

TYPICAL

MAKE SURE THAT THE LENGHT COMPENSATION IS DONE CLOSE TO THE APU

DUCTS COUPLING OR TO THE APU DUCT RETAINER RINGS

06

A

A

D

D

06

06

(399)

805

602

610

610

602

609

A

A

NOTE:

04 TORQUE VALUE 0.25m.daN (22lbf.in)

04

F_SB_364033_6_BJAA_04_01

F

G

MIN 50.8 mm

(2.00 in)

MAX 80.0 mm

(3.15 in)

12.7 mm

(0.49 in)

16.5 mm

(0.65 in)

A A

TYPICAL

Figure A-GBJAA - Sheet 04

Installation of the Sensing Elements in the Rear Fuselage Section

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 721

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 001 thru 002

359HF

358HF

360HF

359HF

04

04

04

04

02

02

02

02

02

02

393

392

59

394

393

59

05

05

05

05

607

612

607

(612)

612

607

607

(612)

02

NOTE:

SECURE WITH LOCKWIRE (MAT. NO. 19−018)

04 TORQUE VALUE 0.25m.daN (22lbf.in)

05 BOND WITH ADHESIVE (MAT. NO. 08−078) AND

PROTECT WITH VARNISH (MAT. NO. 07−003C)

F_SB_364033_6_BJAA_05_01

59

TYPICAL

07 INSTALL THE BRACKET WITHIN THE GIVEN TOLERANCE AREA

4.8 mm TO 7.9 mm

(0.19 in TO 0.31 in)

9.5 mm TO 12.7 mm

(0.37 in TO 0.50 in)

07

07

H

K

J

J

J

Figure A-GBJAA - Sheet 05

Installation of the Sensing Elements in the Rear Fuselage Section

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 722

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 001 thru 002

B

B

361HF

34HF

360HF

140HF

FWD

04

L

D

360HF

361HF

34HF

M

M

N

N

02

02

02

05

04

02

02

59

394

496

405

607

612

607

(612)

602

A

A

A

A

02

NOTE:

SECURE WITH LOCKWIRE (MAT. NO. 19−018)

04 TORQUE VALUE 0.25m.daN (22lbf.in)

05 BOND WITH ADHESIVE (MAT. NO. 08−078) AND

PROTECT WITH VARNISH (MAT. NO. 07−003C)

591

374

F_SB_364033_6_BJAA_06_02

J

Figure A-GBJAA - Sheet 06

Installation of the Sensing Elements in the Rear Fuselage Section

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 723

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 001 thru 002

TYPICAL

STGR5RH

STGR6RH

STGR7RH

STGR9RH

34HF

361HF

FR93 N

P

P Q

P

B B

(399)

(621)

372

313

682

372

609

602

602

602

08 TORQUE VALUE 0.40m.daN (35lbf.in)

NOTE:

08

F_SB_364033_6_BJAA_07_01

Figure A-GBJAA - Sheet 07

Installation of the Sensing Elements in the Rear Fuselage Section

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 724

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 001 thru 002

TYPICAL

P

640

372

372

682

416

640

640

373 372

416

682

682

416

372

602

602

602

602

Q

373

F_SB_364033_6_BJAA_08_02

TYPICAL

NOTE:

FR83 TO FR95

09 STANDARD CLAMP INSTALLATION FOR REMAINING AREAS.

FOR ALL OTHER CLAMP INSTALLATIONS REFER TO THE 

RELATED DETAILS.

09 R

04 TORQUE VALUE 0.25m.daN (22lbf.in)

(399)

(601)

357

04

602

Figure A-GBJAA - Sheet 08

Installation of the Sensing Elements in the Rear Fuselage Section

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 725

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 003 thru 004

Z310

A

MAKE SURE THAT THE SENSING ELEMENTS ARE INSTALLED IN FRONT

OF THE APU DUCT VENTILATION HOLES

FR80

FR83

FR85

FR86

FR88

FR91

FR93

FR95

FR98

FR100

34HF

361HF

140HF

139HF

33HF

358HF

359HF

360HF

B

C

E

G

G

01

NOTE:

K

L

F

M

361

360

365

362

370

369

363

365

/82

F_SB_364033_6_BJAC_01_01

A

01

STANDARD

CLAMP

INSTALLATION

F

H

S

Figure A-GBJAC - Sheet 01

Installation of the Sensing Elements in the Rear Fuselage Section

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 726

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 003 thru 004

FWD

D

E

04

596 604

355

608

405 496

405

602

02 02

02

02

OVERHEAT SENSING

ELEMENT 358HF

B

597

05

C 02

NOTE:

SECURE WITH LOCKWIRE (MAT. NO. 19−018)

03 NUT, PART OF ITEM 355

04 TORQUE VALUE 0.25m.daN (22lbf.in)

05 BOND WITH ADHESIVE (MAT. NO. 08−078) AND

PROTECT WITH VARNISH (MAT. NO. 07−003C)

03

F_SB_364033_6_BJAC_02_01

Figure A-GBJAC - Sheet 02

Installation of the Sensing Elements in the Rear Fuselage Section

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 727

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 003 thru 004

TYPICAL

E

(609)

(603)

(609)

(620)

357

602

357

602

NOTE:

04 TORQUE VALUE 0.25m.daN (22lbf.in)

04

04

D

F_SB_364033_6_BJAC_03_01

Figure A-GBJAC - Sheet 03

Installation of the Sensing Elements in the Rear Fuselage Section

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 728

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 003 thru 004

TYPICAL

(399)

609

357

354

602

MAKE SURE THAT THE LENGHT COMPENSATION IS DONE CLOSE TO THE APU

DUCTS COUPLING OR TO THE APU DUCT RETAINER RINGS

06

NOTE:

04 TORQUE VALUE 0.25m.daN (22lbf.in)

04

F_SB_364033_6_BJAC_04_01

TYPICAL

A

06 A

06

A

A

F

MIN 50.8 mm

(2.00 in)

MAX 80.0 mm

(3.15 in)

12.7 mm

(0.49 in)

16.5 mm

(0.65 in)

A A

TYPICAL

G

G

G

Figure A-GBJAC - Sheet 04

Installation of the Sensing Elements in the Rear Fuselage Section

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 729

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 003 thru 004

360HF

359HF

393

394

607

612

607

(612)

04

04

02

02

02

59

05

05

L

359HF

358HF

K

602

610

610

805

602

(399) (609)

04

393

392

607

612

607

59

(612) 04

04

02

02

02

05

05

F_SB_364033_6_BJAC_05_01

H

59

TYPICAL

4.8 mm TO 7.9 mm

(0.19 in TO 0.31 in)

9.5 mm TO 12.7 mm

(0.37 in TO 0.50 in)

07

07

J

02

NOTE:

SECURE WITH LOCKWIRE (MAT. NO. 19−018)

04 TORQUE VALUE 0.25m.daN (22lbf.in)

05 BOND WITH ADHESIVE (MAT. NO. 08−078) AND

PROTECT WITH VARNISH (MAT. NO. 07−003C)

07 INSTALL THE BRACKET WITHIN THE GIVEN TOLERANCE AREA

J

J

Figure A-GBJAC - Sheet 05

Installation of the Sensing Elements in the Rear Fuselage Section

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 730

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 003 thru 004

E

B

B

361HF

34HF

360HF

140HF

361HF

FWD

M

N

P

P

04

04

361HF

34HF

374

59

607

591

607

612

612

02

02

02

02

N

394

A

A

A

A

05

02

NOTE:

SECURE WITH LOCKWIRE (MAT. NO. 19−018)

04 TORQUE VALUE 0.25m.daN (22lbf.in)

05 BOND WITH ADHESIVE (MAT. NO. 08−078) AND

PROTECT WITH VARNISH (MAT. NO. 07−003C)

J

F_SB_364033_6_BJAC_06_02

Figure A-GBJAC - Sheet 06

Installation of the Sensing Elements in the Rear Fuselage Section

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 731

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 003 thru 004

TYPICAL

STGR5RH

STGR6RH

STGR7RH

STGR9RH

34HF

361HF

P

R Q

Q

Q

FR93

B B

602

609 372

602

602

372

682

313

(399)

(621)

08 TORQUE VALUE 0.40m.daN (35lbf.in)

NOTE:

08

F_SB_364033_6_BJAC_07_01

Figure A-GBJAC - Sheet 07

Installation of the Sensing Elements in the Rear Fuselage Section

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 732

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 003 thru 004

TYPICAL

602

640

372

602

416

682

372

602

640

640

373

373

372

602

682

416

682

416

372

Q

R

F_SB_364033_6_BJAC_08_01

(399)

397

357

04 314

TYPICAL

NOTE:

FR83 TO FR95

09 STANDARD CLAMP INSTALLATION FOR REMAINING AREAS.

FOR ALL OTHER CLAMP INSTALLATIONS REFER TO THE 

RELATED DETAILS.

09

04 TORQUE VALUE 0.25m.daN (22lbf.in)

S

602

Figure A-GBJAC - Sheet 08

Installation of the Sensing Elements in the Rear Fuselage Section

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 733

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 005

Z310

A

MAKE SURE THAT THE SENSING ELEMENTS ARE INSTALLED IN FRONT

OF THE APU DUCT VENTILATION HOLES

FR80

FR83

FR85

FR86

FR88

FR91

FR93

FR95

FR98

FR100

34HF

361HF

140HF

139HF

33HF

358HF

359HF

360HF

B

01

NOTE:

C

F

F

G F

J P

K

L

367

368

362

365

361

360

365

363

/82

F_SB_364033_6_BJAE_01_01

A

01

STANDARD

CLAMP

INSTALLATION

G

S

Figure A-GBJAE - Sheet 01

Installation of the Sensing Elements in the Rear Fuselage Section

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 734

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 005

FWD

D

03

OVERHEAT SENSING

ELEMENT 358HF

B

02

02

02

608

596

604

597

355

405 496

405

602

C

05

02

NOTE:

SECURE WITH LOCKWIRE (MAT. NO. 19−018)

03 NUT, PART OF ITEM 355

04 TORQUE VALUE 0.25m.daN (22lbf.in)

05 BOND WITH ADHESIVE (MAT. NO. 08−078) AND

PROTECT WITH VARNISH (MAT. NO. 07−003C)

04

F_SB_364033_6_BJAE_02_01

Figure A-GBJAE - Sheet 02

Installation of the Sensing Elements in the Rear Fuselage Section

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 735

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 005

F_SB_364033_6_BJAE_03_00

D

E

FR83

E

640

396

396

314

359

640

396

396

314

640

396

357

602

314

602

NOTE:

04 TORQUE VALUE 0.25m.daN (22lbf.in)

04

Figure A-GBJAE - Sheet 03

Installation of the Sensing Elements in the Rear Fuselage Section

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 736

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 005

F_SB_364033_6_BJAE_04_01

MAKE SURE THAT THE LENGTH COMPENSATION IS DONE CLOSE TO THE APU

DUCTS COUPLING OR TO THE APU DUCT RETAINER RINGS

06

59

H

TYPICAL

H

MIN 50.8 mm

(2.00 in)

MAX 80.0 mm

(3.15 in)

12.7 mm

(0.49 in)

16.5 mm

(0.65 in)

A A

TYPICAL

4.8 mm TO 7.9 mm

(0.19 in TO 0.31 in)

9.5 mm TO 12.7 mm

(0.37 in TO 0.50 in)

07

07

A

06 A

06

A

A

TYPICAL

F

P

P

07 INSTALL THE BRACKET WITHIN THE GIVEN TOLERANCE AREA

02

NOTE:

SECURE WITH LOCKWIRE

04 TORQUE VALUE 0.25m.daN (22lbf.in)

05 BOND WITH ADHESIVE (MAT. NO. 08−078) AND

PROTECT WITH VARNISH (MAT. NO. 07−003C)

(MAT. NO. 19−018)

359HF

358HF

04

04

02

02

02

393

392

607

612

607

59

(599)

05

05

G

Figure A-GBJAE - Sheet 04

Installation of the Sensing Elements in the Rear Fuselage Section

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 737

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 005

360HF

359HF

04

04

K

02

02

02

610

805

602

610

602

394

393

607

612

607

59

(399) (609)

(599)

J

05

05

02

NOTE:

SECURE WITH LOCKWIRE (MAT. NO. 19−018)

04 TORQUE VALUE 0.25m.daN (22lbf.in)

05 BOND WITH ADHESIVE (MAT. NO. 08−078) AND

PROTECT WITH VARNISH (MAT. NO. 07−003C)

04

F_SB_364033_6_BJAE_05_01

H

Figure A-GBJAE - Sheet 05

Installation of the Sensing Elements in the Rear Fuselage Section

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 738

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 005

B

B

361HF

34HF

360HF

140HF

361HF

FWD

04

04

L

M

N

N

P

361HF

34HF

607

59

374

591

607

612

394

(599) 02

02

02

02

02

M

A

A

A

A

05

02

NOTE:

SECURE WITH LOCKWIRE (MAT. NO. 19−018)

04 TORQUE VALUE 0.25m.daN (22lbf.in)

05 BOND WITH ADHESIVE (MAT. NO. 08−078) AND

PROTECT WITH VARNISH (MAT. NO. 07−003C)

H

F_SB_364033_6_BJAE_06_02

Figure A-GBJAE - Sheet 06

Installation of the Sensing Elements in the Rear Fuselage Section

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 739

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 005

TYPICAL STGR5RH

STGR6RH

STGR7RH

STGR9RH

34HF

361HF

R Q

Q

Q

FR93

TYPICAL

N

P

B B

(399)

(436)

(609)

(620)

609 372

602

682

313 372

602

602

357

602

08 TORQUE VALUE 0.40m.daN (35lbf.in)

NOTE:

04 TORQUE VALUE 0.25m.daN (22lbf.in)

04

08

F_SB_364033_6_BJAE_07_01

Figure A-GBJAE - Sheet 07

Installation of the Sensing Elements in the Rear Fuselage Section

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 740

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 005

TYPICAL

640

602

372

602

416

682

372

640

640

373

602

372

416

682

373

372

602

682

416

R

Q

F_SB_364033_6_BJAE_08_01

TYPICAL

NOTE:

FR83 TO FR95

09 STANDARD CLAMP INSTALLATION FOR REMAINING AREAS.

FOR ALL OTHER CLAMP INSTALLATIONS REFER TO THE 

RELATED DETAILS.

09

04 TORQUE VALUE 0.25m.daN (22lbf.in)

S

397

357

314

(399)

04

602

Figure A-GBJAE - Sheet 08

Installation of the Sensing Elements in the Rear Fuselage Section

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 741

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 001 thru 002

Z310

A

FR80

FR83

FR86

FR88

FR91

FR93 FR95

FR98

FR100

01

NOTE:

CLOSED BY ADHESIVE STRIP

02 POSITION OF BLOWOUT APERTURE UNDER THE SENSING ELEMENT

01

02

01

02

01

02

01

02

01

02

01

01

01

A

01

F_SB_364033_6_BKAA_01_00

379

376

375

377

378

380

384

381

382 /82

Figure A-GBKAA - Sheet 01

Installation of the Sleeves at the APU Bleed Air Duct

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 742

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 003 thru 005

Z310

A

F_SB_364033_6_BKAC_01_00

FR80

FR83

FR86

FR88

FR91

FR93 FR95

FR98

FR100

01

NOTE:

CLOSED BY ADHESIVE STRIP

02 POSITION OF BLOWOUT APERTURE UNDER THE SENSING ELEMENT

A

01

02

01

02

01

02

01

02

01

02

01

02 01

01

380

382

383

384

385

386

377

387

/82

Figure A-GBKAC - Sheet 01

Installation of the Sleeves at the APU Bleed Air Duct

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 743

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 005

Z310

A

F_SB_364033_6_BLAE_01_00

FR80

FR83

FR84

149HF

D

B

E

C

B

FR83

C

(6 POS)

TYPICAL

D

149HF

150HF

151HF

F

(541)

(419)

(540) (612)

(493)

(494)

(544)

(542)

(612)

(543)

(610) (602)

(494)

(601)

(357)

(602)

(494)

(601)

/82

STGR11RH

A

Figure A-GBLAE - Sheet 01

Removal of the Sensing Element, FIN 149HF, installed with Service Bulletin No. A340-36-4028

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 744

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 005

F_SB_364033_6_BLAE_02_00

FWD

FWD

BEFORE

AFTER

FR84

FR83

FR83

FR84

150HF

151HF

5865VSB

5865VSA

5865VSA

E

F

(479)

(480)

(481)

401

402

479

480

481 5865VB /1S

5865VB /1S

STGR11RH

STGR11RH

(542)

(543)

Figure A-GBLAE - Sheet 02

Removal of the Sensing Element, FIN 149HF, installed with Service Bulletin No. A340-36-4028

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 745

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 001 thru 004

Z310

A

VIEW LOOKING FWD

mm

DIMENSIONS

(in)

B

A

B

C

D

C

D 35.0

12.0

DIA 13.5

C

MIN 15.0

SENSING ELEMENT HOLE

SENSING ELEMENT HOLE

0.47

DIA 0.53

MIN 0.59

1.38

B

FR80

01

NOTE:

DIMENSION FOR CONTROL ONLY

A

B

01

A /82

F_SB_364033_6_BMAA_01_01

Figure A-GBMAA - Sheet 01

Hole Location and Dimensions for the sensing element Installation in the Sheet Metal Pressure

Bulkhead

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 746

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 005

Z310

A

mm

DIMENSIONS

(in)

B

A

C

A

DIA 13.5

B

MIN 24.0

62.0

C

SENSING ELEMENT HOLE

SENSING ELEMENT HOLE

VIEW LOOKING AFT

DIA 0.53

MIN 0.95

2.44

B

A

B

FR80/82

F_SB_364033_6_BMAE_01_01

Figure A-GBMAE - Sheet 01

Hole Location and Dimensions for the Sensing Element Installation in the CFK Pressure Bulkhead

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 747

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF ALL

F_SB_364033_6_BNAA_01_00

TOLERANCES FOR WAVINESS AND BEND IN WIRES

C

B

A E

C

E A

E

A

C

D

E

E

E

E

C

NOTE:

FOR DIMENSIONS, REFER TO SHEET 2

C

C

Figure A-GBNAA - Sheet 01

Tolerances for the Waviness and Bend in the Electrical Wiring

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 748

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF ALL

F_SB_364033_6_BNAA_02_00

E

mm

DIMENSIONS

(in)

C

D

E

B

A

9.52

MAX 6.4

MIN 12.7 MIN 0.50

MIN 25.4 MIN 1.00

MIN R 25.4 MIN R 1.00

MAX 0.25

0.38

E

01

NOTE:

USE OTHER HOLE OF BRACKET IF NECESSARY

02

01

02

ROTATE CLIP FOR SMOOTH ROUTING OF SENSING ELEMENT IF NECESSARY

E

F

E

F MAX 203.0 MAX 7.99

Figure A-GBNAA - Sheet 02

Tolerances for the Waviness and Bend in the Electrical Wiring

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 749

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 001 thru 004

EXISTING WIRE

ADDED WIRE

UNLESS OTHERWISE SPECIFIED PREFIX ALL WIRE

UNLESS OTHERWISE SPECIFIED ALL WIRES ARE CF24 GAUGE

AFTER

A

ZONE 132

A

A

ZONE 122

5401

5402−DM24

ZONE 152 ZONE 270 ZONE 310 ZONE 313

A

IDENTIFICATION WITH ATA−NO. 3622

UNLESS OTHERWISE SPECIFIED ALL ROUTES ARE 2S

AFTER

5400

NOTE:

FR20 FR38

2712VC 3520VC

3506VC

55

72

66

69

FR56 FR80 FR93

37

3672VC

5208VP

/82

804VU

5410VS A

F_SB_364033_6_WAAA_01_00

Figure A-GWAAA - Sheet 01

Wiring Diagram

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 750

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 005

EXISTING WIRE

UNLESS OTHERWISE SPECIFIED PREFIX ALL WIRE

UNLESS OTHERWISE SPECIFIED ALL WIRES ARE CF24 GAUGE

IDENTIFICATION WITH ATA−NO. 3622

UNLESS OTHERWISE SPECIFIED ALL ROUTES ARE 2S

DELETED WIRE

BEFORE

5050−YY18−(150HF)

5051−YY18−(151HF)

5003 5052

ZONE 313

ZONE 311

ZONE 311

ZONE 310

ZONE 313 1S

5003 1S 9

ZONE 151

FR56

A 3677VC

5207VP

149HF

FR80/82 FR83 FR93

NOTE:

5865VS B

5865VS A

ZONE 270

5151VS A

F_SB_364033_6_WAAE_01_00

Figure A-GWAAE - Sheet 01

Wiring Diagram

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 751

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 005

EXISTING WIRE

REROUTED WIRE

UNLESS OTHERWISE SPECIFIED PREFIX ALL WIRE

UNLESS OTHERWISE SPECIFIED ALL WIRES ARE CF24 GAUGE

IDENTIFICATION WITH ATA−NO. 3622

UNLESS OTHERWISE SPECIFIED ALL ROUTES ARE 2S

NOTE:

5003 5052

ZONE 313

ZONE 311

ZONE 310 ZONE 313

AFTER

FR80 FR83 FR93

5207VP

/82

1S

5003 1S 9

ZONE 151

FR56

A 3677VC

ZONE 270

5151VS A

5865VS A

F_SB_364033_6_WAAE_02_00

Figure A-GWAAE - Sheet 02

Wiring Diagram

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 752

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 001 thru 004

A = ADDED WIRE

122 2712VC−A 55 EN3155−003F2222 3622− 5400 2S CF24 14300 563.4 132 3520VC 66 EN3155−008M2222 A

122 2712VC−A 72 EN3155−003F2222 3622− 5401 2S CF24 14300 563.4 132 3506VC 69 EN3155−008M2222 A

152 3672VC 37 EN3155−008M2222 3622−5402 2S DM24 28000 1103.2 313 5410VS A NSA936809RG0001 A

152 3672VC 1 − 2842−5362 2S 311 5215VC −Q BEFORE/AFTER

310 5208VT 4K − 2842−5370 2S 311 5215VC −P BEFORE/AFTER

310 5208VT 6K − 2842−7857 2S 311 5215VC −N BEFORE/AFTER

311 2842−7857 − 2842−5388 2S 311 5215VC −M BEFORE/AFTER

152 3672VC 6 − 2842−5364 2S 311 5215VC −G BEFORE/AFTER

310 5208VT 1G − 2842−5372 2S 311 5215VC −F BEFORE/AFTER

310 5208VT 3J − 2842−7859 2S 311 5215VC −E BEFORE/AFTER

311 2842−7859 − −

−

2842−5390 2S 311 5215VC −D BEFORE/AFTER

152 3672VC 7 − 2842−5365 2S 311 5215VC −C BEFORE/AFTER

310 5208VT 1E − 2842−5373 2S 311 5215VC −B BEFORE/AFTER

310 5208VT 3H − 2842−7860 2S 311 5215VC −A BEFORE/AFTER

311 2842−7860 − − 2842−5391 2S 311 5215VC Z BEFORE/AFTER

152 3672VC 9 − 2842−5367 2S 311 5215VC U BEFORE/AFTER

310 5208VT 1C − 2842−5375 2S 311 5215VC T BEFORE/AFTER

310 5208VT 2H − 2842−7862 2S 311 5215VC S BEFORE/AFTER

311 2842−7862 − − 2842−5393 2S 311 5215VC R BEFORE/AFTER

152 3672VC 8 − 2842−5366 2S 311 5215VC Y BEFORE/AFTER

310 5208VT 1D − 2842−5374 2S 311 5215VC X BEFORE/AFTER

310 5208VT 3G − 2842−7861 2S 311 5215VC W BEFORE/AFTER

311 2842−7861 − − 2842−5392 2S 311 5215VC V BEFORE/AFTER

152 3672VC 10 − 2842−5368 2S 311 5215VC P BEFORE/AFTER

310 5208VT 1B − 2842−5376 2S 311 5215VC N BEFORE/AFTER

ELT. EQUIPMENT F9297000500000 "SHEET 1 ISSUE D"

L

I

N

E ZONE OR

PANEL TERM. TERMINAL P/N WIREIDENT C0L ROUTE GAUGE

LENGTH

MM INCH

ZONE OR

PANEL

ELEC.

IDENT TERM. TERMINAL P/N

INSTRUCTIONS

END 1 LEAD END 2

10

11

12

13

14

15

16

17

18

19

20

21

22

23

24

25

1

2

3

4

5

6

7

8

9

ELEC.

IDENT.

Figure A-GHAAA - Sheet 01

Hook-up Chart

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 753

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 005

A = ADDED WIRE

D = DELETED WIRE

122 2712VC−A 55 EN3155−003F2222 3622− 5400 2S CF24 14300 563.4 132 3520VC 66 EN3155−008M2222 A

122 2712VC−A 72 EN3155−003F2222 3622− 5401 2S CF24 14300 563.4 132 3506VC 69 EN3155−008M2222 A

152 3672VC 37 EN3155−008M2222 3622−5402 2S DM24 28000 1103.2 313 5410VS A NSA936809RG0001 A

151 3677VC 9 − 3622−5003 1S 311 NSA936809RG0001 BEFORE/AFTER

313 5151VS A − 3622−5052 1S 311 NSA936809RG0001

5865VS

5865VS A

2 A

2 AFTER

313 5151VS A − 3622−5052 1S 311 5865VS B NSA936809RG0001 BEFORE

3672VC 1 − 2842−5362 2S 311 5215VC −Q BEFORE/AFTER

5208VT 4K − 2842−5370 2S 311 5215VC −P BEFORE/AFTER

310 5208VT 6K − 2842−7857 2S 311 5215VC −N BEFORE/AFTER

311 2842−7857 − 2842−5388 2S 311 5215VC −M BEFORE/AFTER

152 3672VC 6 − 2842−5364 2S 311 5215VC −G BEFORE/AFTER

310 5208VT 1G − 2842−5372 2S 311 5215VC −F BEFORE/AFTER

310 5208VT 3J − 2842−7859 2S 311 5215VC −E BEFORE/AFTER

311 2842−7859 − −

−

2842−5390 2S 311 5215VC −D BEFORE/AFTER

152 3672VC 7 − 2842−5365 2S 311 5215VC −C BEFORE/AFTER

310 5208VT 1E − 2842−5373 2S 311 5215VC −B BEFORE/AFTER

310 5208VT 3H − 2842−7860 2S 311 5215VC −A BEFORE/AFTER

311 2842−7860 − − 2842−5391 2S 311 5215VC Z BEFORE/AFTER

152 3672VC 9 − 2842−5367 2S 311 5215VC U BEFORE/AFTER

152 3672VC 8 − 2842−5366 2S 311 5215VC Y BEFORE/AFTER

310 5208VT 1D − 2842−5374 2S 311 5215VC X BEFORE/AFTER

310 5208VT 3G − 2842−7861 2S 311 5215VC W BEFORE/AFTER

311 2842−7861 − − 2842−5392 2S 311 5215VC V BEFORE/AFTER

310

152

311

311

5865VS

5865VS

A

B

−

−

3622−5051

3622−5050

1S

1S

311

311

149HF

149HF

D

D

ELT. EQUIPMENT F9297000500200 "SHEET 3 ISSUE D"

L

I

N

E ZONE OR

PANEL TERM. TERMINAL P/N WIREIDENT C0L ROUTE GAUGE

LENGTH

MM INCH

ZONE OR

PANEL

ELEC.

IDENT TERM. TERMINAL P/N

INSTRUCTIONS

END 1 LEAD END 2

10

11

12

13

14

15

16

17

18

19

20

21

22

23

24

25

1

2

3

4

5

6

7

8

9

ELEC.

IDENT.

Figure A-GHAAB - Sheet 01

Hook-up Chart

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 754

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 001 thru 004

310 5208VT 2G − 2842−7863 2S 311 5215VC M BEFORE/AFTER

311 2842−7863 − − 2842−5394 2S 311 5215VC L BEFORE/AFTER

ELT. EQUIPMENT F9297000500000 "SHEET 2 ISSUE G"

151 3677VC 9 − 3622−5003 1S 313 5151VS A BEFORE/AFTER

313 5151VS A − 3622−5004 1S 313 34HF BEFORE/AFTER

313 5410VS A 3622−5403 2S YY18 313 361HF A

L

I

N

E ZONE OR

PANEL TERM. TERMINAL P/N WIREIDENT C0L ROUTE GAUGE

LENGTH

MM INCH

ZONE OR

PANEL

ELEC.

IDENT TERM. TERMINAL P/N

INSTRUCTIONS

END 1 LEAD END 2

10

11

12

13

14

15

16

17

18

19

20

21

22

23

24

25

1

2

3

4

5

6

7

8

9

ELEC.

IDENT.

Figure A-GHBAA - Sheet 01

Hook-up Chart

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 755

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 005

310 5208VT 2G − 2842−7863 2S 311 5215VC M BEFORE/AFTER

311 2842−7863 − − 2842−5394 2S 311 5215VC L BEFORE/AFTER

311 2842−7862 − − 2842−5393 2S 311 5215VC R BEFORE/AFTER

152 3672VC 10 − 2842−5368 2S 311 5215VC P BEFORE/AFTER

310 5208VT 1B − 2842−5376 2S 311 5215VC N BEFORE/AFTER

310 5208VT 1C − 2842−5375 2S 311 5215VC T BEFORE/AFTER

310 5208VT 2H − 2842−7862 2S 311 5215VC S BEFORE/AFTER

ELT. EQUIPMENT F9297000500200 "SHEET 4 ISSUE G"

313 5151VS A − 3622−5004 1S 313 34HF BEFORE/AFTER

313 5410VS A 3622−5403 2S YY18 313 361HF A

L

I

N

E ZONE OR

PANEL TERM. TERMINAL P/N WIREIDENT C0L ROUTE GAUGE

LENGTH

MM INCH

ZONE OR

PANEL

ELEC.

IDENT TERM. TERMINAL P/N

INSTRUCTIONS

END 1 LEAD END 2

10

11

12

13

14

15

16

17

18

19

20

21

22

23

24

25

1

2

3

4

5

6

7

8

9

ELEC.

IDENT.

Figure A-GHBAB - Sheet 01

Hook-up Chart

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 756

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Appendix 01: Elapsed Time Assumptions

**CONF ALL

For detail concerning the elapsed time assumptions, refer to the Gantt chart shown in the next page:

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 1

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Appendix 01: Elapsed Time Assumptions

**CONF 001

ELAPSED TIME ASSUMPTIONS SERVICE BULLETIN No. A340−36−4033

SB ELAPSED TIME

(HOURS)

MH ET/S

TOTAL MANHOURS

SB ELAPSED TIME

268.75

144.00

STEPS

0 75

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.

ARE NOT REFLECTED IN THIS GANTT CHART.

01

02

NOTES:

PER

:

: IF A VSB IS INVOLVED, THE ASSOCIATED MANHOURS

GET ACCESS 27.75 4 7.00

2.00 1.00 2

MODIFICATION OF THE WIRING IN 800VU

REMOVAL OF THE DUCTS BETWEEN FR43 AND FR45 

INSTALLATION OF THE NEW BRACKETS FOR THE ROUTING

INSTALLATION OF THE DUCTS BETWEEN FR43 AND FR45

INSTALLATION OF THE SENSING ELEMENTS AND THE

REMOVAL OF THE DUCTS BETWEEN FR39 AND FR40 FOR

4.00 2.00 2

4.00 4.00 1

4.00 4.00 1

4.00 4.00 1

4.00 4.00 1

1.00 1.00 1

1.00 1.00 1

1.00 1.00 1

2.00 2.00 1

1.00 1.00 1

3.00 3.00 1

1.00 1.00 1

2.00 2.00 1

14.00 14.00 1

14.00 14.00 1

21.00 21.00 1

14.00 14.00 1

1.00 1.00 1

5 15 25 35 45 55 65 80 85 90 95 10 20 30 40 50 60 70 100 105 110 115 120 125 130 135 140 145

MODIFICATION OF THE WIRING BETWEEN AVIONICS 

COMPARTMENT AND THE CARGO COMPARTMENT

REMOVAL OF THE SENSING ELEMENTS AND THE 

SUPPORTS BETWEEN FR39 AND FR44

REMOVAL OF THE SENSING ELEMENTS AND THE 

SUPPORTS BETWEEN FR44 AND FR51

REMOVAL OF THE SENSING ELEMENTS AND THE 

SUPPORTS BETWEEN FR51 AND FR53.6

REMOVAL OF THE SENSING ELEMENTS AND THE

SUPPORTS BETWEEN FR53.6 AND FR55

REMOVAL OF THE DUCTS BETWEEN FR53.5 AND FR53.6

FOR ACCESS

DRILLING OF A NEW HOLE IN THE STRUCTURE BETWEEN

FR53.5 AND FR53.6

INSTALLATION OF A NEW SUPPORT FOR THE ROUTING OF

THE SENSING ELEMENTS BETWEEN FR53.5 AND FR53.6

INSTALLATION OF THE DUCTS BETWEEN FR53.5 AND 

FR53.6

FOR ACCESS

REPLACEMENT OF THE WEB ASSY AND THE HALF CLAMP

ASSY AT FR44

OF THE SENSING ELEMENTS AT FR44

SUPPORTS BETWEEN FR39 AND FR44

INSTALLATION OF THE SENSING ELEMENTS AND THE

SUPPORTS BETWEEN FR44 AND FR50

INSTALLATION OF THE SENSING ELEMENTS AND THE

SUPPORTS BETWEEN FR50 AND FR53.6

INSTALLATION OF THE SENSING ELEMENTS AND THE

SUPPORTS BETWEEN FR53.6 AND FR55

ACCESS

F_SB_364033_6_GAAA_01_00

Figure A-GGAAA - Sheet 01

Gantt Chart

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 2

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Appendix 01: Elapsed Time Assumptions

**CONF 001

ELAPSED TIME ASSUMPTIONS SERVICE BULLETIN No. A340−36−4033

SB ELAPSED TIME

(HOURS)

MH ET/S

TOTAL MANHOURS

SB ELAPSED TIME

268.75

144.00

STEPS

0 75

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.

ARE NOT REFLECTED IN THIS GANTT CHART.

01

02

NOTES:

PER

:

: IF A VSB IS INVOLVED, THE ASSOCIATED MANHOURS

3.00 3.00 1

3.00 3.00 1

INSTALLATION OF THE NEW HARNESS 2SG

INSTALLATION OF THE DUCTS BETWEEN FR39 AND FR40

INSTALLATION OF THE SLEEVES AT THE APU BLEED AIR

TEST

26.00 13.00 2

7.50 3.50 2

11.00 2 5.50

4.50 4.50 1

3.00 3.00 1

14.00 2 7.00

5.25 5.25 1

0.75 0.75 1

11.25 11.25 1

2.00 2.00 1

2.75 2.75 1

5.75 5.75 1

0.50 0.50 1

5.00 5.00 1

37.75 4 9.50

5 15 25 35 45 55 65 80 85 90 95 10 20 30 40 50 60 70 100 105 110 115 120 125 130 135 140 145

INSTALLATION OF THE INTERCONNECTING ELECTRICAL

WIRE FIN 309HF AND 310HF

INSTALLATION OF THE ELECTRICAL WIRING IN THE FWD

CARGO COMPARTMENT

INSTALLATION OF THE ELECTRICAL WIRING IN THE AFT

CARGO COMPARTMENT AND BULK CARGO COMPARTMENT

MODIFICATION OF THE ELECTRICAL WIRING IN THE AFT

AND BULK CARGO COMPARTMENT AND REAR FUSELAGE

INSTALLATION OF AN ADDITIONAL PROFILE IN THE REAR

FUSELAGE SECTION

INSTALLATION OF THE ELECTRICAL WIRING IN THE REAR

FUSELAGE SECTION

REMOVAL OF THE SENSING ELEMENTS IN THE AFT AND

BULK CARGO COMPARTMENT

DRILLING OF AN ADDITIONAL HOLE FOR THE DUAL LOOP

 IN THE SHEET METAL PRESSURE BULKHEAD

INSTALLATION OF THE SENSING ELEMENTS IN THE AFT

AND BULK CARGO COMPARTMENTS

REMOVAL OF THE SENSING ELEMENTS IN THE REAR

FUSELAGE

CLOSE−UP

F_SB_364033_6_GAAA_02_00

INSTALLATION OF THE NEW SUPPORTS FOR THE NEW

HARNESS BETWEEN FR39.1 AND FR39.2

INSTALLATION OF THE SENSING ELEMENTS IN THE REAR

FUSELAGE

DUCT

Figure A-GGAAA - Sheet 02

Gantt Chart

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 3

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Appendix 01: Elapsed Time Assumptions

**CONF 002

ELAPSED TIME ASSUMPTIONS SERVICE BULLETIN No. A340−36−4033

SB ELAPSED TIME

(HOURS)

MH ET/S

TOTAL MANHOURS

SB ELAPSED TIME

268.75

144.00

STEPS

0 75

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.

ARE NOT REFLECTED IN THIS GANTT CHART.

01

02

NOTES:

PER

:

: IF A VSB IS INVOLVED, THE ASSOCIATED MANHOURS

GET ACCESS 27.75 4 7.00

2.00 1.00 2

MODIFICATION OF THE WIRING IN 800VU

REMOVAL OF THE DUCTS BETWEEN FR43 AND FR45 

INSTALLATION OF THE NEW BRACKETS FOR THE ROUTING

INSTALLATION OF THE DUCTS BETWEEN FR43 AND FR45

INSTALLATION OF THE SENSING ELEMENTS AND THE

REMOVAL OF THE DUCTS BETWEEN FR39 AND FR40 FOR

4.00 2.00 2

4.00 4.00 1

4.00 4.00 1

4.00 4.00 1

4.00 4.00 1

1.00 1.00 1

1.00 1.00 1

1.00 1.00 1

2.00 2.00 1

1.00 1.00 1

3.00 3.00 1

1.00 1.00 1

2.00 2.00 1

14.00 14.00 1

14.00 14.00 1

21.00 21.00 1

14.00 14.00 1

1.00 1.00 1

5 15 25 35 45 55 65 80 85 90 95 10 20 30 40 50 60 70 100 105 110 115 120 125 130 135 140 145

MODIFICATION OF THE WIRING BETWEEN AVIONICS 

COMPARTMENT AND THE CARGO COMPARTMENT

REMOVAL OF THE SENSING ELEMENTS AND THE 

SUPPORTS BETWEEN FR39 AND FR44

REMOVAL OF THE SENSING ELEMENTS AND THE 

SUPPORTS BETWEEN FR44 AND FR51

REMOVAL OF THE SENSING ELEMENTS AND THE 

SUPPORTS BETWEEN FR51 AND FR53.6

REMOVAL OF THE SENSING ELEMENTS AND THE

SUPPORTS BETWEEN FR53.6 AND FR55

REMOVAL OF THE DUCTS BETWEEN FR53.5 AND FR53.6

FOR ACCESS

DRILLING OF A NEW HOLE IN THE STRUCTURE BETWEEN

FR53.5 AND FR53.6

INSTALLATION OF A NEW SUPPORT FOR THE ROUTING OF

THE SENSING ELEMENTS BETWEEN FR53.5 AND FR53.6

INSTALLATION OF THE DUCTS BETWEEN FR53.5 AND 

FR53.6

FOR ACCESS

REPLACEMENT OF THE WEB ASSY AND THE HALF CLAMP

ASSY AT FR44

OF THE SENSING ELEMENTS AT FR44

SUPPORTS BETWEEN FR39 AND FR44

INSTALLATION OF THE SENSING ELEMENTS AND THE

SUPPORTS BETWEEN FR44 AND FR50

INSTALLATION OF THE SENSING ELEMENTS AND THE

SUPPORTS BETWEEN FR50 AND FR53.6

INSTALLATION OF THE SENSING ELEMENTS AND THE

SUPPORTS BETWEEN FR53.6 AND FR55

ACCESS

F_SB_364033_6_GAAB_01_00

Figure A-GGAAB - Sheet 01

Gantt Chart

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 4

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Appendix 01: Elapsed Time Assumptions

**CONF 002

ELAPSED TIME ASSUMPTIONS SERVICE BULLETIN No. A340−36−4033

SB ELAPSED TIME

(HOURS)

MH ET/S

TOTAL MANHOURS

SB ELAPSED TIME

268.75

144.00

STEPS

0 75

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.

ARE NOT REFLECTED IN THIS GANTT CHART.

01

02

NOTES:

PER

:

: IF A VSB IS INVOLVED, THE ASSOCIATED MANHOURS

3.00 3.00 1

3.00 3.00 1

INSTALLATION OF THE NEW HARNESS 2SG

INSTALLATION OF THE DUCTS BETWEEN FR39 AND FR40

INSTALLATION OF THE SLEEVES AT THE APU BLEED AIR

TEST

26.00 13.00 2

7.50 3.50 2

11.00 2 5.50

4.50 4.50 1

3.00 3.00 1

14.00 2 7.00

5.25 5.25 1

0.75 0.75 1

11.25 11.25 1

2.00 2.00 1

2.75 2.75 1

5.75 5.75 1

0.50 0.50 1

5.00 5.00 1

37.75 4 9.50

5 15 25 35 45 55 65 80 85 90 95 10 20 30 40 50 60 70 100 105 110 115 120 125 130 135 140 145

INSTALLATION OF THE INTERCONNECTING ELECTRICAL

WIRE FIN 309HF AND 310HF

INSTALLATION OF THE ELECTRICAL WIRING IN THE FWD

CARGO COMPARTMENT

INSTALLATION OF THE ELECTRICAL WIRING IN THE AFT

CARGO COMPARTMENT AND BULK CARGO COMPARTMENT

MODIFICATION OF THE ELECTRICAL WIRING IN THE AFT

AND BULK CARGO COMPARTMENT AND REAR FUSELAGE

INSTALLATION OF AN ADDITIONAL PROFILE IN THE REAR

FUSELAGE SECTION

INSTALLATION OF THE ELECTRICAL WIRING IN THE REAR

FUSELAGE SECTION

REMOVAL OF THE SENSING ELEMENTS IN THE AFT AND

BULK CARGO COMPARTMENT

DRILLING OF AN ADDITIONAL HOLE FOR THE DUAL LOOP

 IN THE SHEET METAL PRESSURE BULKHEAD

INSTALLATION OF THE SENSING ELEMENTS IN THE AFT

AND BULK CARGO COMPARTMENTS

REMOVAL OF THE SENSING ELEMENTS IN THE REAR

FUSELAGE

CLOSE−UP

INSTALLATION OF THE NEW SUPPORTS FOR THE NEW

HARNESS BETWEEN FR39.1 AND FR39.2

INSTALLATION OF THE SENSING ELEMENTS IN THE REAR

FUSELAGE

DUCT

F_SB_364033_6_GAAB_02_00

Figure A-GGAAB - Sheet 02

Gantt Chart

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 5

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Appendix 01: Elapsed Time Assumptions

**CONF 003

ELAPSED TIME ASSUMPTIONS SERVICE BULLETIN No. A340−36−4033

SB ELAPSED TIME

(HOURS)

MH ET/S

TOTAL MANHOURS

SB ELAPSED TIME

268.75

144.00

STEPS

0 75

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.

ARE NOT REFLECTED IN THIS GANTT CHART.

01

02

NOTES:

PER

:

: IF A VSB IS INVOLVED, THE ASSOCIATED MANHOURS

GET ACCESS 27.75 4 7.00

2.00 1.00 2

MODIFICATION OF THE WIRING IN 800VU

REMOVAL OF THE DUCTS BETWEEN FR43 AND FR45 

INSTALLATION OF THE NEW BRACKETS FOR THE ROUTING

INSTALLATION OF THE DUCTS BETWEEN FR43 AND FR45

INSTALLATION OF THE SENSING ELEMENTS AND THE

REMOVAL OF THE DUCTS BETWEEN FR39 AND FR40 FOR

4.00 2.00 2

4.00 4.00 1

4.00 4.00 1

4.00 4.00 1

4.00 4.00 1

1.00 1.00 1

1.00 1.00 1

1.00 1.00 1

2.00 2.00 1

1.00 1.00 1

3.00 3.00 1

1.00 1.00 1

2.00 2.00 1

14.00 14.00 1

14.00 14.00 1

21.00 21.00 1

14.00 14.00 1

1.00 1.00 1

5 15 25 35 45 55 65 80 85 90 95 10 20 30 40 50 60 70 100 105 110 115 120 125 130 135 140 145

MODIFICATION OF THE WIRING BETWEEN AVIONICS 

COMPARTMENT AND THE CARGO COMPARTMENT

REMOVAL OF THE SENSING ELEMENTS AND THE 

SUPPORTS BETWEEN FR39 AND FR44

REMOVAL OF THE SENSING ELEMENTS AND THE 

SUPPORTS BETWEEN FR44 AND FR51

REMOVAL OF THE SENSING ELEMENTS AND THE 

SUPPORTS BETWEEN FR51 AND FR53.6

REMOVAL OF THE SENSING ELEMENTS AND THE

SUPPORTS BETWEEN FR53.6 AND FR55

REMOVAL OF THE DUCTS BETWEEN FR53.5 AND FR53.6

FOR ACCESS

DRILLING OF A NEW HOLE IN THE STRUCTURE BETWEEN

FR53.5 AND FR53.6

INSTALLATION OF A NEW SUPPORT FOR THE ROUTING OF

THE SENSING ELEMENTS BETWEEN FR53.5 AND FR53.6

INSTALLATION OF THE DUCTS BETWEEN FR53.5 AND 

FR53.6

FOR ACCESS

REPLACEMENT OF THE WEB ASSY AND THE HALF CLAMP

ASSY AT FR44

OF THE SENSING ELEMENTS AT FR44

SUPPORTS BETWEEN FR39 AND FR44

INSTALLATION OF THE SENSING ELEMENTS AND THE

SUPPORTS BETWEEN FR44 AND FR50

INSTALLATION OF THE SENSING ELEMENTS AND THE

SUPPORTS BETWEEN FR50 AND FR53.6

INSTALLATION OF THE SENSING ELEMENTS AND THE

SUPPORTS BETWEEN FR53.6 AND FR55

ACCESS

F_SB_364033_6_GAAC_01_00

Figure A-GGAAC - Sheet 01

Gantt Chart

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 6

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Appendix 01: Elapsed Time Assumptions

**CONF 003

ELAPSED TIME ASSUMPTIONS SERVICE BULLETIN No. A340−36−4033

SB ELAPSED TIME

(HOURS)

MH ET/S

TOTAL MANHOURS

SB ELAPSED TIME

268.75

144.00

STEPS

0 75

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.

ARE NOT REFLECTED IN THIS GANTT CHART.

01

02

NOTES:

PER

:

: IF A VSB IS INVOLVED, THE ASSOCIATED MANHOURS

3.00 3.00 1

3.00 3.00 1

INSTALLATION OF THE NEW HARNESS 2SG

INSTALLATION OF THE DUCTS BETWEEN FR39 AND FR40

INSTALLATION OF THE SLEEVES AT THE APU BLEED AIR

TEST

26.00 13.00 2

7.50 3.50 2

11.00 2 5.50

4.50 4.50 1

3.00 3.00 1

14.00 2 7.00

5.25 5.25 1

0.75 0.75 1

11.25 11.25 1

2.00 2.00 1

2.75 2.75 1

5.75 5.75 1

0.50 0.50 1

5.00 5.00 1

37.75 4 9.50

5 15 25 35 45 55 65 80 85 90 95 10 20 30 40 50 60 70 100 105 110 115 120 125 130 135 140 145

INSTALLATION OF THE INTERCONNECTING ELECTRICAL

WIRE FIN 309HF AND 310HF

INSTALLATION OF THE ELECTRICAL WIRING IN THE FWD

CARGO COMPARTMENT

INSTALLATION OF THE ELECTRICAL WIRING IN THE AFT

CARGO COMPARTMENT AND BULK CARGO COMPARTMENT

MODIFICATION OF THE ELECTRICAL WIRING IN THE AFT

AND BULK CARGO COMPARTMENT AND REAR FUSELAGE

INSTALLATION OF AN ADDITIONAL PROFILE IN THE REAR

FUSELAGE SECTION

INSTALLATION OF THE ELECTRICAL WIRING IN THE REAR

FUSELAGE SECTION

REMOVAL OF THE SENSING ELEMENTS IN THE AFT AND

BULK CARGO COMPARTMENT

DRILLING OF AN ADDITIONAL HOLE FOR THE DUAL LOOP

 IN THE SHEET METAL PRESSURE BULKHEAD

INSTALLATION OF THE SENSING ELEMENTS IN THE AFT

AND BULK CARGO COMPARTMENTS

REMOVAL OF THE SENSING ELEMENTS IN THE REAR

FUSELAGE

CLOSE−UP

INSTALLATION OF THE NEW SUPPORTS FOR THE NEW

HARNESS BETWEEN FR39.1 AND FR39.2

INSTALLATION OF THE SENSING ELEMENTS IN THE REAR

FUSELAGE

DUCT

F_SB_364033_6_GAAC_02_00

Figure A-GGAAC - Sheet 02

Gantt Chart

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 7

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Appendix 01: Elapsed Time Assumptions

**CONF 004

ELAPSED TIME ASSUMPTIONS SERVICE BULLETIN No. A340−36−4033

SB ELAPSED TIME

(HOURS)

MH ET/S

TOTAL MANHOURS

SB ELAPSED TIME

268.75

144.00

STEPS

0 75

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.

ARE NOT REFLECTED IN THIS GANTT CHART.

01

02

NOTES:

PER

:

: IF A VSB IS INVOLVED, THE ASSOCIATED MANHOURS

GET ACCESS 27.75 4 7.00

2.00 1.00 2

MODIFICATION OF THE WIRING IN 800VU

REMOVAL OF THE DUCTS BETWEEN FR43 AND FR45 

INSTALLATION OF THE NEW BRACKETS FOR THE ROUTING

INSTALLATION OF THE DUCTS BETWEEN FR43 AND FR45

INSTALLATION OF THE SENSING ELEMENTS AND THE

REMOVAL OF THE DUCTS BETWEEN FR39 AND FR40 FOR

4.00 2.00 2

4.00 4.00 1

4.00 4.00 1

4.00 4.00 1

4.00 4.00 1

1.00 1.00 1

1.00 1.00 1

1.00 1.00 1

2.00 2.00 1

1.00 1.00 1

3.00 3.00 1

1.00 1.00 1

2.00 2.00 1

14.00 14.00 1

14.00 14.00 1

21.00 21.00 1

14.00 14.00 1

1.00 1.00 1

5 15 25 35 45 55 65 80 85 90 95 10 20 30 40 50 60 70 100 105 110 115 120 125 130 135 140 145

MODIFICATION OF THE WIRING BETWEEN AVIONICS 

COMPARTMENT AND THE CARGO COMPARTMENT

REMOVAL OF THE SENSING ELEMENTS AND THE 

SUPPORTS BETWEEN FR39 AND FR44

REMOVAL OF THE SENSING ELEMENTS AND THE 

SUPPORTS BETWEEN FR44 AND FR51

REMOVAL OF THE SENSING ELEMENTS AND THE 

SUPPORTS BETWEEN FR51 AND FR53.6

REMOVAL OF THE SENSING ELEMENTS AND THE

SUPPORTS BETWEEN FR53.6 AND FR55

REMOVAL OF THE DUCTS BETWEEN FR53.5 AND FR53.6

FOR ACCESS

DRILLING OF A NEW HOLE IN THE STRUCTURE BETWEEN

FR53.5 AND FR53.6

INSTALLATION OF A NEW SUPPORT FOR THE ROUTING OF

THE SENSING ELEMENTS BETWEEN FR53.5 AND FR53.6

INSTALLATION OF THE DUCTS BETWEEN FR53.5 AND 

FR53.6

FOR ACCESS

REPLACEMENT OF THE WEB ASSY AND THE HALF CLAMP

ASSY AT FR44

OF THE SENSING ELEMENTS AT FR44

SUPPORTS BETWEEN FR39 AND FR44

INSTALLATION OF THE SENSING ELEMENTS AND THE

SUPPORTS BETWEEN FR44 AND FR50

INSTALLATION OF THE SENSING ELEMENTS AND THE

SUPPORTS BETWEEN FR50 AND FR53.6

INSTALLATION OF THE SENSING ELEMENTS AND THE

SUPPORTS BETWEEN FR53.6 AND FR55

ACCESS

F_SB_364033_6_GAAD_01_00

Figure A-GGAAD - Sheet 01

Gantt Chart

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 8

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Appendix 01: Elapsed Time Assumptions

**CONF 004

ELAPSED TIME ASSUMPTIONS SERVICE BULLETIN No. A340−36−4033

SB ELAPSED TIME

(HOURS)

MH ET/S

TOTAL MANHOURS

SB ELAPSED TIME

268.75

144.00

STEPS

0 75

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.

ARE NOT REFLECTED IN THIS GANTT CHART.

01

02

NOTES:

PER

:

: IF A VSB IS INVOLVED, THE ASSOCIATED MANHOURS

3.00 3.00 1

3.00 3.00 1

INSTALLATION OF THE NEW HARNESS 2SG

INSTALLATION OF THE DUCTS BETWEEN FR39 AND FR40

INSTALLATION OF THE SLEEVES AT THE APU BLEED AIR

TEST

26.00 13.00 2

7.50 3.50 2

11.00 2 5.50

4.50 4.50 1

3.00 3.00 1

14.00 2 7.00

5.25 5.25 1

0.75 0.75 1

11.25 11.25 1

2.00 2.00 1

2.75 2.75 1

5.75 5.75 1

0.50 0.50 1

5.00 5.00 1

37.75 4 9.50

5 15 25 35 45 55 65 80 85 90 95 10 20 30 40 50 60 70 100 105 110 115 120 125 130 135 140 145

INSTALLATION OF THE INTERCONNECTING ELECTRICAL

WIRE FIN 309HF AND 310HF

INSTALLATION OF THE ELECTRICAL WIRING IN THE FWD

CARGO COMPARTMENT

INSTALLATION OF THE ELECTRICAL WIRING IN THE AFT

CARGO COMPARTMENT AND BULK CARGO COMPARTMENT

MODIFICATION OF THE ELECTRICAL WIRING IN THE AFT

AND BULK CARGO COMPARTMENT AND REAR FUSELAGE

INSTALLATION OF AN ADDITIONAL PROFILE IN THE REAR

FUSELAGE SECTION

INSTALLATION OF THE ELECTRICAL WIRING IN THE REAR

FUSELAGE SECTION

REMOVAL OF THE SENSING ELEMENTS IN THE AFT AND

BULK CARGO COMPARTMENT

DRILLING OF AN ADDITIONAL HOLE FOR THE DUAL LOOP

 IN THE SHEET METAL PRESSURE BULKHEAD

INSTALLATION OF THE SENSING ELEMENTS IN THE AFT

AND BULK CARGO COMPARTMENTS

REMOVAL OF THE SENSING ELEMENTS IN THE REAR

FUSELAGE

CLOSE−UP

INSTALLATION OF THE NEW SUPPORTS FOR THE NEW

HARNESS BETWEEN FR39.1 AND FR39.2

INSTALLATION OF THE SENSING ELEMENTS IN THE REAR

FUSELAGE

DUCT

F_SB_364033_6_GAAD_02_00

Figure A-GGAAD - Sheet 02

Gantt Chart

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 9

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Appendix 01: Elapsed Time Assumptions

**CONF 005

ELAPSED TIME ASSUMPTIONS SERVICE BULLETIN No. A340−36−4033

SB ELAPSED TIME

(HOURS)

MH ET/S

TOTAL MANHOURS

SB ELAPSED TIME

273.00

144.00

STEPS

0 75

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.

ARE NOT REFLECTED IN THIS GANTT CHART.

01

02

NOTES:

PER

:

: IF A VSB IS INVOLVED, THE ASSOCIATED MANHOURS

GET ACCESS 27.75 4 7.00

2.00 1.00 2

MODIFICATION OF THE WIRING IN 800VU

REMOVAL OF THE DUCTS BETWEEN FR43 AND FR45 

INSTALLATION OF THE NEW BRACKETS FOR THE ROUTING

INSTALLATION OF THE DUCTS BETWEEN FR43 AND FR45

INSTALLATION OF THE SENSING ELEMENTS AND THE

REMOVAL OF THE DUCTS BETWEEN FR39 AND FR40 FOR

4.00 2.00 2

4.00 4.00 1

4.00 4.00 1

4.00 4.00 1

4.00 4.00 1

1.00 1.00 1

1.00 1.00 1

1.00 1.00 1

2.00 2.00 1

1.00 1.00 1

3.00 3.00 1

1.00 1.00 1

2.00 2.00 1

14.00 14.00 1

14.00 14.00 1

21.00 21.00 1

14.00 14.00 1

1.00 1.00 1

5 15 25 35 45 55 65 80 85 90 95 10 20 30 40 50 60 70 100 105 110 115 120 125 130 135 140 145

MODIFICATION OF THE WIRING BETWEEN AVIONICS 

COMPARTMENT AND THE CARGO COMPARTMENT

REMOVAL OF THE SENSING ELEMENTS AND THE 

SUPPORTS BETWEEN FR39 AND FR44

REMOVAL OF THE SENSING ELEMENTS AND THE 

SUPPORTS BETWEEN FR44 AND FR51

REMOVAL OF THE SENSING ELEMENTS AND THE 

SUPPORTS BETWEEN FR51 AND FR53.6

REMOVAL OF THE SENSING ELEMENTS AND THE

SUPPORTS BETWEEN FR53.6 AND FR55

REMOVAL OF THE DUCTS BETWEEN FR53.5 AND FR53.6

FOR ACCESS

DRILLING OF A NEW HOLE IN THE STRUCTURE BETWEEN

FR53.5 AND FR53.6

INSTALLATION OF A NEW SUPPORT FOR THE ROUTING OF

THE SENSING ELEMENTS BETWEEN FR53.5 AND FR53.6

INSTALLATION OF THE DUCTS BETWEEN FR53.5 AND 

FR53.6

FOR ACCESS

REPLACEMENT OF THE WEB ASSY AND THE HALF CLAMP

ASSY AT FR44

OF THE SENSING ELEMENTS AT FR44

SUPPORTS BETWEEN FR39 AND FR44

INSTALLATION OF THE SENSING ELEMENTS AND THE

SUPPORTS BETWEEN FR44 AND FR50

INSTALLATION OF THE SENSING ELEMENTS AND THE

SUPPORTS BETWEEN FR50 AND FR53.6

INSTALLATION OF THE SENSING ELEMENTS AND THE

SUPPORTS BETWEEN FR53.6 AND FR55

ACCESS

F_SB_364033_6_GAAE_01_00

Figure A-GGAAE - Sheet 01

Gantt Chart

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 10

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Appendix 01: Elapsed Time Assumptions

**CONF 005

ELAPSED TIME ASSUMPTIONS SERVICE BULLETIN No. A340−36−4033

SB ELAPSED TIME

(HOURS)

MH ET/S

TOTAL MANHOURS

SB ELAPSED TIME

273.00

144.00

STEPS

0 75

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.

ARE NOT REFLECTED IN THIS GANTT CHART.

01

02

NOTES:

PER

:

: IF A VSB IS INVOLVED, THE ASSOCIATED MANHOURS

3.00 3.00 1

3.00 3.00 1

INSTALLATION OF THE NEW HARNESS 2SG

INSTALLATION OF THE DUCTS BETWEEN FR39 AND FR40

INSTALLATION OF THE SLEEVES AT THE APU BLEED AIR

TEST

26.00 13.00 2

7.50 3.50 2

11.00 2 5.50

4.50 4.50 1

3.00 3.00 1

14.00 2 7.00

5.25 5.25 1

0.75 0.75 1

11.25 11.25 1

2.00 2.00 1

2.75 2.75 1

0.50 0.50 1

5.00 5.00 1

37.75 4 9.50

5 15 25 35 45 55 65 80 85 90 95 10 20 30 40 50 60 70 100 105 110 115 120 125 130 135 140 145

INSTALLATION OF THE INTERCONNECTING ELECTRICAL

WIRE FIN 309HF AND 310HF

INSTALLATION OF THE ELECTRICAL WIRING IN THE FWD

CARGO COMPARTMENT

INSTALLATION OF THE ELECTRICAL WIRING IN THE AFT

CARGO COMPARTMENT AND BULK CARGO COMPARTMENT

MODIFICATION OF THE ELECTRICAL WIRING IN THE AFT

AND BULK CARGO COMPARTMENT AND REAR FUSELAGE

INSTALLATION OF AN ADDITIONAL PROFILE IN THE REAR

FUSELAGE SECTION

INSTALLATION OF THE ELECTRICAL WIRING IN THE REAR

FUSELAGE SECTION

REMOVAL OF THE SENSING ELEMENTS IN THE AFT AND

BULK CARGO COMPARTMENT

DRILLING OF AN ADDITIONAL HOLE FOR THE DUAL LOOP

 IN THE SHEET METAL PRESSURE BULKHEAD

INSTALLATION OF THE SENSING ELEMENTS IN THE AFT

AND BULK CARGO COMPARTMENTS

REMOVAL OF THE SENSING ELEMENTS IN THE REAR

FUSELAGE

CLOSE−UP

INSTALLATION OF THE NEW SUPPORTS FOR THE NEW

HARNESS BETWEEN FR39.1 AND FR39.2

DUCT

F_SB_364033_6_GAAE_02_00

REMOVAL OF THE SENSING ELEMENT, FIN 149HF

INSTALLATION OF THE SENSING ELEMENTS IN THE 

4.25 4.25 1

5.75 5.75 1

REAR FUSELAGE

Figure A-GGAAE - Sheet 02

Gantt Chart

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 11

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

REPORTING SHEET

TITLE: PNEUMATIC - LEAK DETECTION - INTRODUCE ADAPTED DUAL LOOP

OVERHEAT LEAK DETECTION APU BLEED AIR DUCT

MODIFICATION No.: 55198D46290 55198D46286 55961D46493 55962D46494 58529D46961

58530D46962

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: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 1

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

QUALITY PERCEPTION FORM

Use this form to tell us what is your perception of the quality of this Service Bulletin. The reported data

that you provide us will be used to analyse areas of difficulties and to take corrective action to further

improve the quality of our Service Bulletins.

We thank you for the time you have taken in completing this form.

(Please rate on a scale of 1 to 4, with 4 being the highest score)

- Quality rating of this SB 4321

- Quality rating of the Accomplishment Instructions 4321

- Quality rating of the Illustrations 4321

- Is this SB easy to understand ? Y/N

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

short description of the issue.

Planning Material Instructions

X Effectivity X Kit content X Preparation

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

X Manpower X Industry support X Test

X References X Re-identification X Close-Up

X Publication X Tooling X Illustrations

Comments:

Operator: Date:

Name/Title:

Please return this form to:

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX FRANCE

Attn : SEM4 Service Bulletins Management

FAX : (33) 5 61 93 42 51

Or via your Resident Customer Support Office.

DATE: Sep 23/11 SERVICE BULLETIN No.: A340-36-4033

REVISION No.: 01 - Jan 28/13 Page: 1

6

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