@A340-500/600

SERVICE BULLETIN

SUMMARY

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX

FRANCE

Tel : (33) 5 61 93 33 33

Telex : AIRBU 530526F

Fax : (33) 5 61 93 42 51

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

MANDATORY MANDATORY MANDATORY

ATA SYSTEM: 57

TITLE: WINGS - CENTER WING BOX - INSPECTION OF THE EXTERNAL

RADIUS ON THE UPPER HORIZONTAL CRUCIFORM FITTING AT

FRAME 47

**CONF ALL

MODIFICATIONS

None

REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

During the A340-600EF2 fatigue test, damages have occurred in external radius on upper horizontal

cruciform in rear corner at Frame 47, on LH and RH sides. These damages were detected after tear

down inspections using High Frequency Eddy Current (HFEC) method.

This condition, if not corrected, could impair the structural integrity of the affected aeroplanes.

This mandated Inspection Service Bulletin (ISB) request to perform a repetitive HFEC inspection of the

external radius on upper horizontal cruciform fitting at Frame 47 on LH and RH sides.

Accomplishment of this Service Bulletin will allow early detection of cracks on upper horizontal cruciform

in rear corner at frame 47, ensuring the structural integrity of the area. Accomplishment of this Service

Bulletin will avoid extensive repairs and related aircraft down time.

GENERAL EVALUATION

EVALUATION TABLE

COMPLIANCE MANDATORY (1) CANCELS INSPECTION SB NO

POTENTIAL AD YES A/C OPERATION AFFECTED NO

RELIABILITY AFFECTED NO PAX COMFORT AFFECTED NO

COST SAVING NO LROPS AFFECTED NO

STRUCTURAL LIFE EXTN NO VENDOR SB INVOLVED NO

NOTE (1): Service Bulletin must be accomplished.

DATE: Feb 25/11 SERVICE BULLETIN No.: A340-57-5029

REVISION No.: 00 - Feb 25/11 Page: 1

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SERVICE BULLETIN

SUMMARY

MATERIAL PRICE INFORMATION

**CONF 001

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Kit 575029A01R00 1 175.00 Bolt, Nut

**CONF 002

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Kit 575029A02R00 1 900.00 Bolt, Nut

EFFECTIVITY

**CONF ALL

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

06U 62X 70U 72W 79W CES CHH DLH ETD HFY IBE QAF QTR

SAA SIA SOR TAM THA UAE VIR

CONCURRENT REQUIREMENTS

None

REFERENCES / REPERCUSSIONS

TFU None

OEB None

AOT None

SIL None

LINE MAINTENANCE AFFECTED No

LIFE LIMIT None

OTHER None

NATURE OF THE WORK

AIRCRAFT YES

EQUIPMENT NO

HARD NO

SOFT NO

OBRM NO

DATE: Feb 25/11 SERVICE BULLETIN No.: A340-57-5029

REVISION No.: 00 - Feb 25/11 Page: 2

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SERVICE BULLETIN

SUMMARY

MANPOWER

**CONF 001

Task 575029-832-801-001: Inspection

TOTAL MANHOURS 20.00

ELAPSED TIME (HOURS) 10.00

**CONF 002

Task 575029-832-801-001: Inspection

TOTAL MANHOURS 20.00

ELAPSED TIME (HOURS) 10.00

APPENDICES

**CONF ALL

Appendix 01 : Inspection Report

Appendix 02 : Elapsed Time Assumption

DATE: Feb 25/11 SERVICE BULLETIN No.: A340-57-5029

REVISION No.: 00 - Feb 25/11 Page: 3

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@A340-500/600

SERVICE BULLETIN

SUMMARY

**CONF ALL

FR40

FR47

B

A

B

LH SIDE SHOWN

RH SIDE SYMMETRICAL

AREA TO BE INSPECTED

NOTE:

200 mm

(7.874 in)

B

EXTERNAL RADIUS

C

POSSIBLE CRACK

C

F_SB_575029_5_SAAA_01_01

UPPER HORIZONTAL

CRUCIFORM FITTING

FR47

A

Figure A-FSAAA - Sheet 01

DATE: Feb 25/11 SERVICE BULLETIN No.: A340-57-5029

REVISION No.: 00 - Feb 25/11 Page: 4

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@A340-500/600

SERVICE BULLETIN

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX

FRANCE

Tel : (33) 5 61 93 33 33

Telex : AIRBU 530526F

Fax : (33) 5 61 93 42 51

MANDATORY MANDATORY MANDATORY

ATA SYSTEM: 57

TITLE: WINGS - CENTER WING BOX - INSPECTION OF THE EXTERNAL

RADIUS ON THE UPPER HORIZONTAL CRUCIFORM FITTING AT

FRAME 47

MODIFICATION No.: None

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

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

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

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

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

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

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

AIRBUS prior written consent.

1. PLANNING INFORMATION

**CONF ALL

A. EFFECTIVITY

(1) Models

340-541 340-542 340-642

(2) Effectivity by MSN

0371 0376 0383 0391 0394 0410 0416-0417 0426 0431 0436 0440 0445 0449 0453

0457 0460 0464 0468 0471 0475 0478 0482 0485 0488 0492 0495 0499 0514 0517

0520 0523 0531 0534 0537 0540 0543 0547 0557 0560 0563 0566 0569 0572 0575

0577 0580 0583 0586 0601 0604 0606 0608 0611 0615 0617 0619 0622 0624 0626

0628 0630 0639 0672 0677 0681 0685 0689 0694 0698 0702 0706 0710 0715 0719

0723 0727 0736 0740 0744 0748 0753 0757 0761-0768 0771 0775 0779 0783 0787

0790 0794 0798 0804 0812 0829 0837 0846 0848 0870 0886 0894 0897 0902 0910

0912 0917 0924 0929 0933 0953 0960 0972 0981 0987 0993 1005 1017 1030 1040

1079 1091 1102 1122

DATE: Feb 25/11 SERVICE BULLETIN No.: A340-57-5029

REVISION No.: 00 - Feb 25/11 Page: 1

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@A340-500/600

SERVICE BULLETIN

(3) Effectivity by Operator

The Operator/MSN relationship is provided for information only and is correct at the time

of issue in accordance with the information available to AIRBUS. Any future changes

resulting from transfer of an aircraft from one operator to another will not be reflected in

this list unless the Service Bulletin is revised for another reason.

OPERATOR MSN

06U 1091 1102

62X 0779

70U 0902

72W 0917

79W 0924

CES 0468 0488 0514 0577 0586

CHH 0436 0453 0475

DLH 0482 0517 0523 0537 0540 0543 0566 0569 0580 0583 0762 0763

0767 0771 0790 0794 0812 0846 0848 0897 0972 0981 0987 1005

ETD 0748 0757 0761 0783 0829 0837 0870 0929 0933 1030 1040

HFY 0910 0912

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

0960 0993 1017 1079 1122

QAF 0495

QTR 0715 0740 0766 0798

SAA 0410 0417 0426 0531 0534 0547 0557 0626 0630

SIA 0478 0492 0499 0560 0563

SOR 0886 0894

TAM 0445 0464

THA 0624 0628 0677 0681 0689 0698 0710 0719 0775 0953

UAE 0394 0457 0471 0485 0520 0572 0608 0611 0685 0694

VIR 0371 0376 0383 0391 0416 0449 0575 0615 0622 0639 0706 0723

0736 0753 0764 0765 0768 0787 0804

(4) Configuration by MSN

MSN CONFIGURATION

0371 0376 0383 0391 0394 0410 0416 0417 0426 0431 0436

0440 0445 0449 0453 0457 0460 0464 0468 0471 0475 0478

0482 0485 0488 0492 0495 0499 0514 0517 0520 0523 0531

0534 0537 0540 0543 0547 0557 0560 0563 0566 0569 0572

0575 0577 0580 0583 0586 0601 0604 0606 0608 0611 0615

0617 0619 0622 0624 0626 0628 0630 0639 0672 0677 0681

0685 0689 0694 0698 0702 0706 0710 0715 0719 0723 0727

0736 0740 0744 0748 0753 0757 0761 0762 0763 0764 0765

0766 0767 0768 0771 0775 0779 0783 0787 0790 0794 0798

0804 0812 0829 0837 0846 0848 0870 0886 0894 0897 0902

0910 0912 0917 0924 0929 0933 0953 0960 0972 0981 0987

0993 1005 1017 1030 1040

001

1079 1091 1102 1122 002

DATE: Feb 25/11 SERVICE BULLETIN No.: A340-57-5029

REVISION No.: 00 - Feb 25/11 Page: 2

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@A340-500/600

SERVICE BULLETIN

(5) Configuration definition

**CONF 001

Config. 001 concerns aircraft on which Mod. No. 57691S19466 (FUSELAGE - CENTER

FUSELAGE - MODIFY UPPER BELLY FAIRING - (PRODUCTION SOL)) is not

embodied.

**CONF 002

Config. 002 concerns aircraft on which Mod. No. 57691S19466 (FUSELAGE - CENTER

FUSELAGE - MODIFY UPPER BELLY FAIRING - (PRODUCTION SOL)) is embodied.

(6) Material Effectivity

**CONF 001

MATERIAL QTY PER A/C SEE NOTES

Kit 575029A01R00 1

Consumable CMLA01 1

**CONF 002

MATERIAL QTY PER A/C SEE NOTES

Kit 575029A02R00 1

Consumable CMLA01 1

**CONF ALL

B. CONCURRENT REQUIREMENTS

None

C. REASON

(1) History

During the A340-600EF2 fatigue test, damages have occurred in external radius on

upper horizontal cruciform in rear corner at Frame 47, on LH and RH sides. These

damages were detected after tear down inspections using High Frequency Eddy Current

(HFEC) method.

This condition, if not corrected, could impair the structural integrity of the affected

aeroplanes.

(2) Objective/Action

This mandated Inspection Service Bulletin (ISB) request to perform a repetitive HFEC

inspection of the external radius on upper horizontal cruciform fitting at Frame 47 on LH

and RH sides.

DATE: Feb 25/11 SERVICE BULLETIN No.: A340-57-5029

REVISION No.: 00 - Feb 25/11 Page: 3

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@A340-500/600

SERVICE BULLETIN

(3) Advantages

Accomplishment of this Service Bulletin will allow early detection of cracks on upper

horizontal cruciform in rear corner at frame 47, ensuring the structural integrity of the

area. Accomplishment of this Service Bulletin will avoid extensive repairs and related

aircraft down time.

(4) Operational/Maintenance Consequences

None

D. DESCRIPTION

To accomplish this Service Bulletin it is necessary to :

**CONF 001

Task 575029-832-801-001: Inspection

(1) Do a Special Detailed Inspection of the External Radius on the Upper Horizontal

Cruciform Fitting at FR 47 (LH side).

(2) Do a Special Detailed Inspection of the External Radius on the Upper Horizontal

Cruciform Fitting at FR 47 (RH side).

**CONF 002

Task 575029-832-801-001: Inspection

(1) Do a Special Detailed Inspection of the External Radius on the Upper Horizontal

Cruciform Fitting at FR 47 (LH side).

(2) Do a Special Detailed Inspection of the External Radius on the Upper Horizontal

Cruciform Fitting at FR 47 (RH side).

**CONF ALL

E. COMPLIANCE

(1) Classification

MANDATORY: Service Bulletin must be accomplished.

(2) Accomplishment Timescale

Accomplishment of this Service Bulletin is expected to be rendered mandatory by the

issue of an Airworthiness Directive (AD) published by the European Aviation Safety

Agency (EASA).

DATE: Feb 25/11 SERVICE BULLETIN No.: A340-57-5029

REVISION No.: 00 - Feb 25/11 Page: 4

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@A340-500/600

SERVICE BULLETIN

COMPLIANCE TIME REPETITIVE

INTERVAL NOT

TO EXCEED

CONDITION ACTION

THRESHOLD GRACE PERIOD

First

accomplishment of

SB 57-5029

Inspect in

accordance with

SUBTASK

575029-250-001

Refer to Table 2

for the threshold

values of the

aircraft to be

inspected

NO Not applicable

Crack found Contact AIRBUS

for further

instructions

Before next flight NO Not applicable

No crack found Repeat the

inspection in

accordance with

SUBTASK

575029-250-001

Not applicable NO Refer to Table 2

for the interval

values of the

aircraft to be reinspected

Table 1. Inspection for Cracks of the Upper Horizontal Cruciform Fitting at FR47.

DATE: Feb 25/11 SERVICE BULLETIN No.: A340-57-5029

REVISION No.: 00 - Feb 25/11 Page: 5

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SERVICE BULLETIN

THRESHOLD

(whichever occurs

first)

REPETITIVE

INTERVAL

(whichever occurs

first)

CRITERIA AIRCRAFT

CONCERNED

FC FH FC FH

Pre Mod. No.

56558S19405 and

pre Mod. No.

48487H14261

all A340-642 WV000

and WV001 aircraft

9,750 63,600 6,200 40,500

Pre Mod. No.

56558S19405 and

post Mod. No.

48487H14261

all A340-642 WV000

and WV001 aircraft

7,050 46,100 4,550 29,700

all A340-642 WV000

and WV001 aircraft

except for all the

aircraft listed below

for which a specific

threshold is defined

6,350 41,500 3,650 24,000

0371 7,235 47,030 3,650 24,000

0376, 0410, 0417,

0426, 0431, 0440,

0449 and 0460

6,395 51,170 3,650 24,000

0383, 0391 and 0416 6,380 51,170 3,650 24,000

0436 7,050 47,030 3,650 24,000

Post Mod. No.

56558S19405 and

pre Mod. No.

48487H14261

0453 6,350 51,170 3,650 24,000

all A340-642 WV000

and WV001 aircraft

except for all the

aircraft listed below

for which a specific

threshold is defined

4,600 30,000 2,700 17,500

0475, 0482, 0517,

0523, 0531, 0534,

0537, 0540, 0543,

0547, 0557, 0566,

0569, 0575, 0580,

0583, 0601, 0604,

0606, 0615, 0617,

0619, 0622, 0626,

0630, 0639, 0672,

0702, 0706, 0710

and 0744

4,615 36,950 2,700 17,500

A340-642

Weight

Variant

(WV)000

and

WV001

Post Mod. No.

56558S19405 and

post Mod. No.

48487H14261

0468, 0488, 0514,

0577, 0586, 0677,

0681, 0689 and 0719

5,220 33,950 2,700 17,500

DATE: Feb 25/11 SERVICE BULLETIN No.: A340-57-5029

REVISION No.: 00 - Feb 25/11 Page: 6

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SERVICE BULLETIN

THRESHOLD

(whichever occurs

first)

REPETITIVE

INTERVAL

(whichever occurs

first)

CRITERIA AIRCRAFT

CONCERNED

FC FH FC FH

Pre Mod. No.

56558S19405 and

pre Mod. No.

48487H14261

All A340-541 WV000,

WV001, WV002,

WV003 and WV004

aircraft

9,700 73,900 6,050 46,200

Pre Mod. No.

56558S19405 and

post Mod. No.

48487H14261

All A340-541 WV000,

WV001, WV002,

WV003 and WV004

aircraft

7,100 54,200 4,500 34,400

all A340-541 WV000,

WV001, WV002,

WV003 and WV004

aircraft except for all

the aircraft listed

below for which a

specific threshold is

defined

6,350 48,400 3,550 27,400

0394 and 0457 7,235 55,170 3,550 27,400

0471 7,205 55,170 3,550 27,400

445 6,830 54,610 3,550 27,400

Post Mod. No.

56558S19405 and

pre Mod. No.

48487H14261

464 6,965 54,640 3,550 27,400

all A340-541 WV000,

WV001, WV002,

WV003 and WV004

aircraft except for all

the aircraft listed

below for which a

specific threshold is

defined

4,650 35,500 2,650 20,500

0478 and 0492 5,205 40,320 2,650 20,500

0485, 0520, 0572,

0608, 0611, 0685

and 0694

5,285 40,320 2,650 20,500

0499 5,240 40,320 2,650 20,500

0560 5,145 40,300 2,650 20,500

0563 5,190 40,320 2,650 20,500

0624 5,170 40,320 2,650 20,500

0628 5,115 40,320 2,650 20,500

A340-541

Weight

Variant

(WV)000,

WV001,

WV002,

WV003

and

WV004

Post Mod. No.

56558S19405 and

post Mod. No.

48487H14261

0698 5,080 40,320 2,650 20,500

DATE: Feb 25/11 SERVICE BULLETIN No.: A340-57-5029

REVISION No.: 00 - Feb 25/11 Page: 7

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SERVICE BULLETIN

THRESHOLD

(whichever occurs

first)

REPETITIVE

INTERVAL

(whichever occurs

first)

CRITERIA AIRCRAFT

CONCERNED

FC FH FC FH

Pre Mod. No.

(56558S19405 and

56026S19358 and

56026S19415 and

56633S19416)

all A340-642 WV101,

WV102 and WV103

and A340-643

WV101, WV102 and

WV103 aircraft

8,400 58,000 5,350 37,000

all A340-642 WV101,

WV102 and WV103

and A340-643

WV101, WV102 and

WV103 aircraft

except for all the

aircraft listed below

for which a specific

threshold is defined

4,800 33,100 2,700 18,600

A340-642

Weight

Variant

(WV)101,

WV102

and

WV103

and

A340-643

WV101,

WV102

and

WV103

Post Mod. No.

(56558S19405 or

56026S19358 or

56026S19415 or

56633S19416)

0762, 0763, 0767

and 0771

5,420 38,880 2,700 18,600

Pre Mod. No.

(56558S19405 and

56633S19416)

all A340-541 WV101,

WV102 and WV103

and A340-542

WV101, WV102 and

WV103 aircraft

A340-541 7,800 62,500 4,750 38,200

Weight

Variant

(WV)101,

WV102

and

WV103

and

A340-542

WV101,

WV102

and

WV103

Post Mod. No.

(56558S19405 or

56633S19416)

all A340-541 WV101,

WV102 and WV103

and A340-542

WV101, WV102 and

WV103 aircraft

4,450 35,600 2,350 19,000

Table 2. Threshold and repetitive interval.

NOTE: The thresholds for aircraft post Mod. No. 56558S19405 (Service Bulletin

No. A340-57-5010 accomplished) must be counted from the aircraft first

flight and not from Service Bulletin No. A340-57-5010 accomplishment.

F. APPROVAL

Approved under EASA Design Organisation Approval No. EASA 21J.031.

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

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

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

before incorporation of the Service Bulletin.

DATE: Feb 25/11 SERVICE BULLETIN No.: A340-57-5029

REVISION No.: 00 - Feb 25/11 Page: 8

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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 575029-832-801-001: Inspection

Get Access 4.00

On Aircraft

Do a Special Detailed Inspection of the External

Radius on the Upper Horizontal Cruciform Fitting at FR

47 (LH side).

5.00

Do a Special Detailed Inspection of the External

Radius on the Upper Horizontal Cruciform Fitting at FR

47 (RH side).

5.00

Close-Up 6.00

TOTAL MANHOURS 20.00

ELAPSED TIME (HOURS) 10.00

NOTE: For the details concerning the elapsed time, refer to Appendix 02 : Elapsed

Time Assumption .

**CONF 002

Task 575029-832-801-001: Inspection

Get Access 4.00

On Aircraft

Do a Special Detailed Inspection of the External

Radius on the Upper Horizontal Cruciform Fitting at FR

47 (LH side).

5.00

Do a Special Detailed Inspection of the External

Radius on the Upper Horizontal Cruciform Fitting at FR

47 (RH side).

5.00

Close-Up 6.00

TOTAL MANHOURS 20.00

ELAPSED TIME (HOURS) 10.00

NOTE: For the details concerning the elapsed time, refer to Appendix 02 : Elapsed

Time Assumption .

**CONF ALL

H. WEIGHT AND BALANCE

Not Changed

DATE: Feb 25/11 SERVICE BULLETIN No.: A340-57-5029

REVISION No.: 00 - Feb 25/11 Page: 9

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SERVICE BULLETIN

I. ELECTRICAL LOAD DATA

Not Changed

J. REFERENCES

**CONF 001

Aircraft Maintenance Manual (AMM) 06-20-00 06-31-53 12-34-24

20-21-11 20-28-00 53-35-11

Consumable Material List (CML)

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

Non Destructive Test Manual (NTM) 57-18-07

Service Bulletin (SB) A340-57-5010

Standards Manual (SM)

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

51-43-00 51-44-00

**CONF 002

Aircraft Maintenance Manual (AMM) 06-20-00 06-31-53 12-34-24

20-21-11 20-28-00 53-35-11

Consumable Material List (CML)

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

Non Destructive Test Manual (NTM) 57-18-07

Service Bulletin (SB) A340-57-5010

Standards Manual (SM)

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

51-43-00 51-44-00

**CONF ALL

K. PUBLICATION AFFECTED

Impact on scheduled maintenance : Refer to Maintenance Planning Document (MPD).

L. INTERCHANGEABILITY/MIXABILITY

Not Applicable

M. SPARES

None

DATE: Feb 25/11 SERVICE BULLETIN No.: A340-57-5029

REVISION No.: 00 - Feb 25/11 Page: 10

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SERVICE BULLETIN

2. MATERIAL INFORMATION

**CONF ALL

A. MATERIAL - PRICE AND AVAILABILITY

(1) Procurement Addresses

Kit 575029A01R00 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 Jeager 150

D-22335 Hamburg

Germany

For ordering by internet :

http://spares.airbus.com

For ordering modification kits by fax : +49 40

50 76 25 90

For ordering of single spares by fax : +49 40

50 76 40 13

Kit 575029A02R00 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 Jeager 150

D-22335 Hamburg

Germany

For ordering by internet :

http://spares.airbus.com

For ordering modification kits by fax : +49 40

50 76 25 90

For ordering of single spares by fax : +49 40

50 76 40 13

(2) Price and Availability

Kit 575029A01R00

Cost 175.00 USD

Availability 15 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: Feb 25/11 SERVICE BULLETIN No.: A340-57-5029

REVISION No.: 00 - Feb 25/11 Page: 11

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SERVICE BULLETIN

Kit 575029A02R00

Cost 900.00 USD

Availability 15 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

This Service Bulletin is subject to the Fatigue Test Integration Program. Refer to the FTIP

policy.

C. LIST OF COMPONENTS

Kit 575029A01R00

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

NOTES

3 ASNA2531-3 32 Nut

6 EN6115V3-3 20 Bolt

7 EN6115V3-4 12 Bolt

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 575029A02R00

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

NOTES

2 EN6115V3X4 28 Bolt

3 ASNA2531-3 28 Nut

NOTE: If you find part numbers of hardware components in the related kit(s) which

you cannot identify in the LIST OF COMPONENTS of this Service Bulletin,

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

to part number relationship.

D. LIST OF MATERIALS - OPERATOR SUPPLIED

(1) Consumable Materials

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO CML

MAT. No.

QTY PER A/C SEE

NOTES

Electrical Bonding Coating (blue

Color)

07-001D As required

DATE: Feb 25/11 SERVICE BULLETIN No.: A340-57-5029

REVISION No.: 00 - Feb 25/11 Page: 12

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ITEM DESCRIPTION REFERENCE TO CML

MAT. No.

QTY PER A/C SEE

NOTES

Interfay Sealant 09-005A As required

Sealant-Brush Consistency 09-013 As required

Corrosion Inhibiting fillet

Consistency

09-016 As required

Solvent General Purpose 11-026 As required

(2) Components

None

(3) Equipment

None

E. PARTS TO BE RE-IDENTIFIED BY OPERATOR

None

F. TOOLING

None

DATE: Feb 25/11 SERVICE BULLETIN No.: A340-57-5029

REVISION No.: 00 - Feb 25/11 Page: 13

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This Page Intentionally Left Blank

DATE: Feb 25/11 SERVICE BULLETIN No.: A340-57-5029

REVISION No.: 00 - Feb 25/11 Page: 14

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3. ACCOMPLISHMENT INSTRUCTIONS

Task 575029-832-801-001 - Inspection

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

INCLUDED IN THE REFERENCED PROCEDURES.

CAUTION: ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP

ELECTRICAL WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY

AND MECHANICALLY SERVICEABLE). WHEN YOU DO MAINTENANCE

WORK, REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING,

COMPONENTS AND THE WORK AREA AS CLEAN AS POSSIBLE. TO DO

THIS:

- PUT PROTECTION, SUCH AS PLASTIC SHEETING, CLOTHS, ETC; AS

NECESSARY ON WIRING AND COMPONENTS.

- REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND

OTHER CONTAMINATION.

THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION

AND DAMAGE TO THE ELECTRICAL WIRING INSTALLATION.

IN CASE OF CONTAMINATION REFER TO ESPM 20-55-00.

Task Associated Data

**CONF 001

Zone

147 148

Manpower

TOTAL MANHOURS 20.00

ELAPSED TIME (HOURS) 10.00

**CONF 002

Zone

147 148

Manpower

TOTAL MANHOURS 20.00

ELAPSED TIME (HOURS) 10.00

DATE: Feb 25/11 SERVICE BULLETIN No.: A340-57-5029

REVISION No.: 00 - Feb 25/11 Page: 15

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**CONF ALL

A. GENERAL

**CONF 001

(1) Subtask 575029-910-001-001 - 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

Electrical Bonding Coating

(blue Color)

07-001D As required

Interfay Sealant 09-005A As required

Sealant-Brush Consistency 09-013 As required

Corrosion Inhibiting fillet

Consistency

09-016 As required

Solvent General Purpose 11-026 As required

References

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

06-31-53, Page Block 001

Task 20-21-11-911-801

Task 20-28-00-912-801

Task 20-28-00-912-802

Consumable Material List (CML)

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

Standards Manual (SM)

Structural Repair Manual (SRM) 51-23-12

51-24-00

51-42-00

51-43-00

51-44-00

(a) Refer to Consumable Materials List (CML) for the specification of materials (Mat.

No.) you must use in this Service Bulletin.

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

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

(d) Tag the parts that you must remove and retain to make the subsequent installation.

(e) Put all the retained hardware in identified plastic bags to the related unit.

DATE: Feb 25/11 SERVICE BULLETIN No.: A340-57-5029

REVISION No.: 00 - Feb 25/11 Page: 16

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(f) Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardware

components in the related kit(s) which you cannot identify in the LIST OF

COMPONENTS of this Service Bulletin. The SM will give you the correct part

number to part number relationship.

(g) For the alternative and substitute fasteners (Refer to SRM 51-43-00).

(h) Remove and install the fasteners (Refer to SRM 51-42-00).

(i) Drill and deburr the holes (Refer to SRM 51-44-00).

(j) To torque tighten the standard threaded fasteners (Refer to AMM Task

20-21-11-911-801).

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

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

Solvent General

Purpose

11-026 As required

(m) For the protection, refer to SRM 51-23-12.

(n) Install the fasteners on the structure with :

Sealant-Brush

Consistency

09-013 As required

(wet assembly)

(o) Install the karman webs with interposition of :

Interfay Sealant 09-005A As required

(p) Renew the sealant bead around the supports with :

Corrosion Inhibiting

fillet Consistency

09-016 As required

(q) Do the electrical bonding (Refer to ESPM 20-51-20, AMM Task 20-28-00-912-801

and AMM Task 20-28-00-912-802) and protect with :

Electrical Bonding

Coating (blue Color)

07-001D As required

(2) Subtask 575029-839-001-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

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

Service Bulletin.

DATE: Feb 25/11 SERVICE BULLETIN No.: A340-57-5029

REVISION No.: 00 - Feb 25/11 Page: 17

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**CONF 002

(1) Subtask 575029-910-001-002 - 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

Electrical Bonding Coating

(blue Color)

07-001D As required

Interfay Sealant 09-005A As required

Sealant-Brush Consistency 09-013 As required

Corrosion Inhibiting fillet

Consistency

09-016 As required

Solvent General Purpose 11-026 As required

References

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

06-31-53, Page Block 001

Task 20-21-11-911-801

Task 20-28-00-912-802

Consumable Material List (CML)

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

Standards Manual (SM)

Structural Repair Manual (SRM) 51-23-12

51-24-00

51-42-00

51-43-00

51-44-00

(a) Refer to Consumable Materials List (CML) for the specification of materials (Mat.

No.) you must use in this Service Bulletin.

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

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

(d) Tag the parts that you must remove and retain to make the subsequent installation.

(e) Put all the retained hardware in identified plastic bags to the related unit.

(f) Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardware

components in the related kit(s) which you cannot identify in the LIST OF

COMPONENTS of this Service Bulletin. The SM will give you the correct part

number to part number relationship.

DATE: Feb 25/11 SERVICE BULLETIN No.: A340-57-5029

REVISION No.: 00 - Feb 25/11 Page: 18

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(g) For the alternative and substitute fasteners (Refer to SRM 51-43-00).

(h) Remove and install the fasteners (Refer to SRM 51-42-00).

(i) Drill and deburr the holes (Refer to SRM 51-44-00).

(j) To torque tighten the standard threaded fasteners (Refer to AMM Task

20-21-11-911-801).

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

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

Solvent General

Purpose

11-026 As required

(m) For the protection, refer to SRM 51-23-12.

(n) Install the fasteners on the structure with :

Sealant-Brush

Consistency

09-013 As required

(wet assembly)

(o) Install the karman webs with interposition of :

Interfay Sealant 09-005A As required

(p) Renew the sealant bead around the supports with :

Corrosion Inhibiting

fillet Consistency

09-016 As required

(q) Do the electrical bonding (Refer to ESPM 20-51-20 and AMM Task

20-28-00-912-802) and protect with :

Electrical Bonding

Coating (blue Color)

07-001D As required

(2) Subtask 575029-839-001-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

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

Service Bulletin.

DATE: Feb 25/11 SERVICE BULLETIN No.: A340-57-5029

REVISION No.: 00 - Feb 25/11 Page: 19

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**CONF ALL

B. PREPARATION

**CONF 001

(1) Subtask 575029-941-001-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 12-34-24-860-802

Task 53-35-11-000-801

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

12-34-24-860-802).

(b) Put the access platform(s) in position.

(2) Subtask 575029-010-004-001 - Remove the Karman Web and the Sealant at FR47

(LH side).

Work Zones and Access Panels

Zone Access/Work location

147

Manpower Resources

Skills AIRFRAME

References

Aircraft Maintenance Manual (AMM) Task 53-35-11-000-801

Fig. A-FBBAA

Area to be Inspected

Sheet 01

Fig. A-FBCAA

Removal/Installation of the Karman

Webs at FR47.

Sheet 01

Sheet 02

(a) Remove the wing to fuselage fairing 147AT (Refer to AMM Task

53-35-11-000-801).

(b) Remove :

Refer to Fig. A-FBCAA

10 Blind Rivet Item (4) Discard

6 Blind Rivet Item (5) Discard

1 Web Item (1) Retain

DATE: Feb 25/11 SERVICE BULLETIN No.: A340-57-5029

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(c) Remove the sealant from the area to be inspected, refer to Fig. A-FBBAA Sheet

01.

(3) Subtask 575029-010-002-001 - Remove the Karman Web and the Sealant at FR47

(RH side).

Work Zones and Access Panels

Zone Access/Work location

148

Manpower Resources

Skills AIRFRAME

References

Aircraft Maintenance Manual (AMM) Task 53-35-11-000-801

Fig. A-FBCAA

Removal/Installation of the Karman

Webs at FR47.

Sheet 01

Sheet 02

Fig. A-FBBAA

Area to be Inspected

Sheet 01

(a) Remove the wing to fuselage fairings 148AT (Refer to AMM Task

53-35-11-000-801).

(b) Remove :

Refer to Fig. A-FBCAA

10 Blind Rivet Item (4) Discard

6 Blind Rivet Item (5) Discard

1 Web Item (1) Retain

(c) Remove the sealant from the area to be inspected, refer to Fig. A-FBBAA Sheet

01.

**CONF 002

(1) Subtask 575029-941-001-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 12-34-24-860-802

Task 53-35-11-000-801

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

12-34-24-860-802).

DATE: Feb 25/11 SERVICE BULLETIN No.: A340-57-5029

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(b) Put the access platform(s) in position.

(2) Subtask 575029-010-004-002 - Remove the Karman Web and the Sealant at FR47

(LH side).

Work Zones and Access Panels

Zone Access/Work location

147

Manpower Resources

Skills AIRFRAME

References

Aircraft Maintenance Manual (AMM) Task 53-35-11-000-801

Fig. A-FBBAA

Area to be Inspected

Sheet 01

Fig. A-FBCAB

Removal/Installation of the Karman

Webs at FR47.

Sheet 01

Sheet 02

(a) Remove the wing to fuselage fairing 147AT (Refer to AMM Task

53-35-11-000-801).

(b) Remove :

Refer to Fig. A-FBCAB

14 Bolt Item (2) Discard

14 Nut Item (3) Discard

1 Web Item (1) Retain

(c) Remove the sealant from the area to be inspected, refer to Fig. A-FBBAA Sheet

01.

(3) Subtask 575029-010-002-002 - Remove the Karman Web and the Sealant at FR47

(RH side).

Work Zones and Access Panels

Zone Access/Work location

148

Manpower Resources

Skills AIRFRAME

References

Aircraft Maintenance Manual (AMM) Task 53-35-11-000-801

Fig. A-FBCAB

Removal/Installation of the Karman

Webs at FR47.

Sheet 01

Sheet 02

DATE: Feb 25/11 SERVICE BULLETIN No.: A340-57-5029

REVISION No.: 00 - Feb 25/11 Page: 22

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References

Fig. A-FBBAA

Area to be Inspected

Sheet 01

(a) Remove the wing to fuselage fairings 148AT (Refer to AMM Task

53-35-11-000-801).

(b) Remove :

Refer to Fig. A-FBCAB

14 Bolt Item (2) Discard

14 Nut Item (3) Discard

1 Web Item (1) Retain

(c) Remove the sealant from the area to be inspected, refer to Fig. A-FBBAA Sheet

01.

**CONF ALL

C. PROCEDURE

**CONF 001

(1) Subtask 575029-250-001-001 - Do a Special Detailed Inspection of the External

Radius on the Upper Horizontal Cruciform Fitting at FR 47 (LH side).

Work Zones and Access Panels

Zone Access/Work location

147

Manpower Resources

Manhours 5.00

Minimum number of person 1

Subtask elapsed time 5.00

Skills AIRFRAME

References

Non Destructive Test Manual (NTM) 57-18-07

Fig. A-FBBAA

Area to be Inspected

Sheet 01

Fig. A-FBAAA

Flow Chart

Sheet 01

(a) For the inspection area, refer to Fig. A-FBBAA Sheet 01.

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(b) Do a special detailed inspection of the external radius on the upper horizontal

cruciform fitting at Frame 47 (LH side) as per NTM 57-18-07.

Refer to Fig. A-FBAAA Sheet 01

(c) For the inspection report, refer to Appendix 01 : Inspection Report .

(2) Subtask 575029-250-002-001 - Do a Special Detailed Inspection of the External

Radius on the Upper Horizontal Cruciform Fitting at FR 47 (RH side).

Work Zones and Access Panels

Zone Access/Work location

148

Manpower Resources

Manhours 5.00

Minimum number of person 1

Subtask elapsed time 5.00

Skills AIRFRAME

References

Non Destructive Test Manual (NTM) 57-18-07

Fig. A-FBBAA

Area to be Inspected

Sheet 01

Fig. A-FBAAA

Flow Chart

Sheet 01

(a) For the inspection area, refer to Fig. A-FBBAA Sheet 01.

(b) Do a special detailed inspection of the external radius on the upper horizontal

cruciform fitting at Frame 47 (RH side) as per NTM 57-18-07.

Refer to Fig. A-FBAAA Sheet 01

(c) For the inspection report, refer to Appendix 01 : Inspection Report .

**CONF 002

(1) Subtask 575029-250-001-001 - Do a Special Detailed Inspection of the External

Radius on the Upper Horizontal Cruciform Fitting at FR 47 (LH side).

Work Zones and Access Panels

Zone Access/Work location

147

Manpower Resources

Manhours 5.00

Minimum number of person 1

Subtask elapsed time 5.00

Skills AIRFRAME

DATE: Feb 25/11 SERVICE BULLETIN No.: A340-57-5029

REVISION No.: 00 - Feb 25/11 Page: 24

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References

Non Destructive Test Manual (NTM) 57-18-07

Fig. A-FBBAA

Area to be Inspected

Sheet 01

Fig. A-FBAAA

Flow Chart

Sheet 01

(a) For the inspection area, refer to Fig. A-FBBAA Sheet 01.

(b) Do a special detailed inspection of the external radius on the upper horizontal

cruciform fitting at Frame 47 (LH side) as per NTM 57-18-07.

Refer to Fig. A-FBAAA Sheet 01

(c) For the inspection report, refer to Appendix 01 : Inspection Report .

(2) Subtask 575029-250-002-001 - Do a Special Detailed Inspection of the External

Radius on the Upper Horizontal Cruciform Fitting at FR 47 (RH side).

Work Zones and Access Panels

Zone Access/Work location

148

Manpower Resources

Manhours 5.00

Minimum number of person 1

Subtask elapsed time 5.00

Skills AIRFRAME

References

Non Destructive Test Manual (NTM) 57-18-07

Fig. A-FBBAA

Area to be Inspected

Sheet 01

Fig. A-FBAAA

Flow Chart

Sheet 01

(a) For the inspection area, refer to Fig. A-FBBAA Sheet 01.

(b) Do a special detailed inspection of the external radius on the upper horizontal

cruciform fitting at Frame 47 (RH side) as per NTM 57-18-07.

Refer to Fig. A-FBAAA Sheet 01

(c) For the inspection report, refer to Appendix 01 : Inspection Report .

DATE: Feb 25/11 SERVICE BULLETIN No.: A340-57-5029

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**CONF ALL

D. TEST

**CONF 001

None

**CONF 002

None

**CONF ALL

E. CLOSE-UP

**CONF 001

(1) Subtask 575029-410-001-001 - Install the Karman Web and apply the Sealant at

FR47 (LH side).

Work Zones and Access Panels

Zone Access/Work location

147

Manpower Resources

Manhours 4.00

Minimum number of person 2

Subtask elapsed time 2.00

Skills AIRFRAME

Material necessary to do the job

Kit 575029A01R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

3 ASNA2531-3 16 Nut

6 EN6115V3-3 10 Bolt

7 EN6115V3-4 6 Bolt

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Corrosion Inhibiting fillet

Consistency

09-016 As required

References

Aircraft Maintenance Manual (AMM) Task 53-35-11-400-801

Fig. A-FBBAA

Area to be Inspected

Sheet 01

DATE: Feb 25/11 SERVICE BULLETIN No.: A340-57-5029

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References

Fig. A-FBCAA

Removal/Installation of the Karman

Webs at FR47.

Sheet 01

Sheet 02

(a) Apply the sealant on the inspected area (Refer to Fig. A-FBBAA Sheet 01) :

Corrosion Inhibiting

fillet Consistency

09-016 As required

(b) Put in position :

Refer to Fig. A-FBCAA

1 Web Item (1) Retained at

removal

(c) Oversize the 16 holes to a diameter comprised between 4.78 mm (0.188 in.) and

4.82 mm (0.190 in.) as shown on Fig. A-FBCAA Sheet 01 and Fig. A-FBCAA Sheet

02.

(d) Remove the web Item(1) and clean before final installation.

(e) Install :

Refer to Fig. A-FBCAA

1 Web Item (1) Retained at

removal

10 Bolt EN6115V3-3 Item 6

6 Bolt EN6115V3-4 Item 7

16 Nut ASNA2531-3 Item 3

Apply the protection on the fasteners before installation, refer to SUBTASK

575029-910-001 001 Standard Practices .

(f) Install the wing to fuselage fairing 147AT (Refer to AMM Task 53-35-11-400-801).

(2) Subtask 575029-410-002-001 - Install the Karman Web and apply the Sealant at

FR47 (RH side).

Work Zones and Access Panels

Zone Access/Work location

148

Manpower Resources

Skills AIRFRAME

DATE: Feb 25/11 SERVICE BULLETIN No.: A340-57-5029

REVISION No.: 00 - Feb 25/11 Page: 27

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Material necessary to do the job

Kit 575029A01R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

3 ASNA2531-3 16 Nut

6 EN6115V3-3 10 Bolt

7 EN6115V3-4 6 Bolt

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Corrosion Inhibiting fillet

Consistency

09-016 As required

References

Aircraft Maintenance Manual (AMM) Task 53-35-11-400-801

Fig. A-FBBAA

Area to be Inspected

Sheet 01

Fig. A-FBCAA

Removal/Installation of the Karman

Webs at FR47.

Sheet 01

Sheet 02

(a) Apply the sealant on the inspected area (Refer to Fig. A-FBBAA Sheet 01) :

Corrosion Inhibiting

fillet Consistency

09-016 As required

(b) Put in position :

Refer to Fig. A-FBCAA

1 Web Item (1) Retained at

removal

(c) Oversize the 16 holes to a diameter comprised between 4.78 mm (0.188 in.) and

4.82 mm (0.190 in.) as shown on Fig. A-FBCAA Sheet 01 and Fig. A-FBCAA Sheet

02.

(d) Remove the web Item(1) and clean before final installation.

(e) Install :

Refer to Fig. A-FBCAA

1 Web Item (1) Retained at

removal

10 Bolt EN6115V3-3 Item 6

6 Bolt EN6115V3-4 Item 7

DATE: Feb 25/11 SERVICE BULLETIN No.: A340-57-5029

REVISION No.: 00 - Feb 25/11 Page: 28

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16 Nut ASNA2531-3 Item 3

Apply the protection on the fasteners before installation, refer to SUBTASK

575029-910-001 001 Standard Practices .

(f) Install the wing to fuselage fairing 148AT (Refer to AMM Task 53-35-11-400-801).

(3) Subtask 575029-942-001-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

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

equipment.

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

(c) Remove the access platform(s).

**CONF 002

(1) Subtask 575029-410-001-002 - Install the Karman Web and apply the Sealant at

FR47 (LH side).

Work Zones and Access Panels

Zone Access/Work location

147

Manpower Resources

Manhours 4.00

Minimum number of person 2

Subtask elapsed time 2.00

Skills AIRFRAME

Material necessary to do the job

Kit 575029A02R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

2 EN6115V3X4 14 Bolt

3 ASNA2531-3 14 Nut

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Corrosion Inhibiting fillet

Consistency

09-016 As required

References

Aircraft Maintenance Manual (AMM) Task 53-35-11-400-801

DATE: Feb 25/11 SERVICE BULLETIN No.: A340-57-5029

REVISION No.: 00 - Feb 25/11 Page: 29

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References

Fig. A-FBCAB

Removal/Installation of the Karman

Webs at FR47.

Sheet 01

Sheet 02

Fig. A-FBBAA

Area to be Inspected

Sheet 01

(a) Apply the sealant on the inspected area (Refer to Fig. A-FBBAA Sheet 01) :

Corrosion Inhibiting

fillet Consistency

09-016 As required

(b) Put in position :

Refer to Fig. A-FBCAB

1 Web Item (1) Retained at

removal

(c) Oversize the 14 holes to a diameter comprised between 5.11 in. (0.201 in.) and

5.15 (0.203 in.) as shown on Fig. A-FBCAB Sheet 01 and Fig. A-FBCAB Sheet 02.

(d) Remove the web Item(1) and clean before final installation.

(e) Install :

Refer to Fig. A-FBCAB

1 Web Item (1) Retained at

removal

14 Bolt EN6115V3X4 Item 2

14 Nut ASNA2531-3 Item 3

Apply the protection on the fasteners before installation, refer to SUBTASK

575029-910-001 002 Standard Practices .

(f) Install the wing to fuselage fairing 147AT (Refer to AMM Task 53-35-11-400-801).

(2) Subtask 575029-410-002-002 - Install the Karman Web and apply the Sealant at

FR47 (RH side).

Work Zones and Access Panels

Zone Access/Work location

148

Manpower Resources

Skills AIRFRAME

DATE: Feb 25/11 SERVICE BULLETIN No.: A340-57-5029

REVISION No.: 00 - Feb 25/11 Page: 30

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Material necessary to do the job

Kit 575029A02R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

2 EN6115V3X4 14 Bolt

3 ASNA2531-3 14 Nut

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Corrosion Inhibiting fillet

Consistency

09-016 As required

References

Aircraft Maintenance Manual (AMM) Task 53-35-11-400-801

Fig. A-FBBAA

Area to be Inspected

Sheet 01

Fig. A-FBCAB

Removal/Installation of the Karman

Webs at FR47.

Sheet 01

Sheet 02

(a) Apply the sealant on the inspected area (Refer to Fig. A-FBBAA Sheet 01) :

Corrosion Inhibiting

fillet Consistency

09-016 As required

(b) Put in position :

Refer to Fig. A-FBCAB

1 Web Item (1) Retained at

removal

(c) Oversize the 14 holes to a diameter comprised between 5.11 in. (0.201 in.) and

5.15 (0.203 in.) as shown on Fig. A-FBCAB Sheet 01 and Fig. A-FBCAB Sheet 02.

(d) Remove the web Item(1) and clean before final installation.

(e) Install :

Refer to Fig. A-FBCAB

1 Web Item (1) Retained at

removal

14 Bolt EN6115V3X4 Item 2

14 Nut ASNA2531-3 Item 3

Apply the protection on the fasteners before installation, refer to SUBTASK

575029-910-001 002 Standard Practices .

DATE: Feb 25/11 SERVICE BULLETIN No.: A340-57-5029

REVISION No.: 00 - Feb 25/11 Page: 31

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(f) Install the wing to fuselage fairing 148AT (Refer to AMM Task 53-35-11-400-801).

(3) Subtask 575029-942-001-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

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

equipment.

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

(c) Remove the access platform(s).

DATE: Feb 25/11 SERVICE BULLETIN No.: A340-57-5029

REVISION No.: 00 - Feb 25/11 Page: 32

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**CONF 001

FR40

FR47

B

STGR28

(1)

VIEW LOOKING FWD

LH SIDE SHOWN B RH SIDE SYMMETRICAL

A

B

F_SB_575029_5_BCAA_01_01

UPPER HORIZONTAL

CRUCIFORM FITTING

FR47

A

Figure A-FBCAA - Sheet 01

Removal/Installation of the Karman Webs at FR47.

DATE: Feb 25/11 SERVICE BULLETIN No.: A340-57-5029

REVISION No.: 00 - Feb 25/11 Page: 33

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**CONF 001

HOLE

SYMBOL ITEM PN DESCRIPTION REMARKS

HOLE DIAMETER

MIN MAX

4.78 mm

(0.188 in)

4.82 mm

(0.190 in)

TRANSITION

OLD

ITEM

NEW

FIT (4)

(5)

6

7

N

N

01 APPLY MAT. No. 09−013 ON THE FASTENERS (WET ASSEMBLY).

02 INSTALL THE WEB ITEM WITH INTERFAYING SEALANT MAT No. 09−005A.

03 RENEW SEALANT BEAD WITH MAT No. 09−016.

NOTE:

HEAD ON THE VISIBLE SIDE N

01

01

02

03

03

(1)

4.78 mm

(0.188 in)

4.82 mm

(0.190 in)

TYPICAL VIEW

EN6115V3−3 BOLT

ASNA2531−3 NUT

EN6115V3−4 BOLT

ASNA2531−3 NUT

3

3

TRANSITION

FIT

F_SB_575029_5_BCAA_02_04

Figure A-FBCAA - Sheet 02

Removal/Installation of the Karman Webs at FR47.

DATE: Feb 25/11 SERVICE BULLETIN No.: A340-57-5029

REVISION No.: 00 - Feb 25/11 Page: 34

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**CONF 002

FR40

FR47

B

A

B

(1)

VIEW LOOKING FWD

LH SIDE SHOWN B RH SIDE SYMMETRICAL

F_SB_575029_5_BCAB_01_01

UPPER HORIZONTAL

CRUCIFORM FITTING

FR47

A

Figure A-FBCAB - Sheet 01

Removal/Installation of the Karman Webs at FR47.

DATE: Feb 25/11 SERVICE BULLETIN No.: A340-57-5029

REVISION No.: 00 - Feb 25/11 Page: 35

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**CONF 002

HOLE

SYMBOL ITEM PN DESCRIPTION REMARKS

HOLE DIAMETER

MIN MAX

5.15 mm

(0.203 in)

TRANSITION EN6115V3X4 BOLT

OLD

ITEM

NEW

FIT

(2) 2

F

01 APPLY MAT. No. 09−013 ON THE FASTENERS (WET ASSEMBLY).

02 INSTALL THE WEB ITEM WITH INTERFAYING SEALANT MAT No. 09−005A.

03 RENEW SEALANT BEAD WITH MAT No. 09−016.

NOTE:

HEAD ON HIDDEN SIDE F

01

02

03

03

(3) 3 ASNA2531−3 NUT

(1)

TYPICAL VIEW

5.11 mm

(0.201 in)

F_SB_575029_5_BCAB_02_04

Figure A-FBCAB - Sheet 02

Removal/Installation of the Karman Webs at FR47.

DATE: Feb 25/11 SERVICE BULLETIN No.: A340-57-5029

REVISION No.: 00 - Feb 25/11 Page: 36

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**CONF ALL

FR40

FR47

B

FR47

A

A

B

LH SIDE SHOWN

RH SIDE SYMMETRICAL

01 SEALANT TO REMOVE FOR THE INSPECTION PROCEDURE

AREA TO BE INSPECTED

NOTE:

200 mm

(7.874 in)

B

EXTERNAL RADIUS

UPPER HORIZONTAL

C

POSSIBLE CRACK

01

C

CRUCIFORM FITTING

F_SB_575029_5_BBAA_01_01

Figure A-FBBAA - Sheet 01

Area to be Inspected

DATE: Feb 25/11 SERVICE BULLETIN No.: A340-57-5029

REVISION No.: 00 - Feb 25/11 Page: 37

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**CONF ALL

QUESTION

ACTION

FINDING

YES CRACK NO

DO THE INSPECTION AGAIN

FITTING AT FR47 AT THE THRESHOLDS AND INTERVALS GIVEN IN

THE PLANNING INFORMATION PARAGRAPH E.(2).

DO A SPECIAL DETAILED INSPECTION AS PER NTM 57−18−07 OF

THE EXTERNAL RADIUS ON THE UPPER HORIZONTAL CRUCIFORM

AND FOLLOW THEIR

CONTACT AIRBUS

NO FURTHER ACTION

SEND TO AIRBUS

THE INSPECTION REPORT

WITHIN 90 DAYS

CORRECTIVE ACTION

BEFORE NEXT FLIGHT

F_SB_575029_5_BAAA_01_04

REFER TO APPENDIX 01

SEND TO AIRBUS

THE INSPECTION REPORT

WITHIN 90 DAYS

REFER TO APPENDIX 01

Figure A-FBAAA - Sheet 01

Flow Chart

DATE: Feb 25/11 SERVICE BULLETIN No.: A340-57-5029

REVISION No.: 00 - Feb 25/11 Page: 38

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Appendix 01 : Inspection Report

**CONF ALL

The results of the inspection, including no findings, replacement or action to be done, must be

forwarded to Airbus department SEES1, on the attached inspection report sheet.

DATE: Feb 25/11 SERVICE BULLETIN No.: A340-57-5029

REVISION No.: 00 - Feb 25/11 Page: 1

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Appendix 01 : Inspection Report

**CONF ALL

INSPECTION REPORT

SERVICE BULLETIN No. :

A/C MSN :

FLIGHT CYCLES :

FLIGHT HOURS :

A340−57−5029

DATE OF INSPECTION :

RETURN TO :

AIRBUS

CUSTOMER SERVICES ENGINEERING − SEES1

FUSELAGE (WB/LR) − VERTICAL TAIL PLANE

INSPECTION METHOD :

− CENTER WING BOX (WB/LR)

SPECIAL DETAILED

INSPECTION

1 ROND POINT MAURICE BELLONTE

31707 BLAGNAC CEDEX

FRANCE

FAX +33 (0)5 61 93 3614

PLEASE RECORD OTHER FINDINGS :

LH SIDE

YES NO

CRACK

RH SIDE

YES NO

F_SB_575029_5_AAAA_01_00

Figure A-FAAAA - Sheet 01

Inspection Report

DATE: Feb 25/11 SERVICE BULLETIN No.: A340-57-5029

REVISION No.: 00 - Feb 25/11 Page: 2

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Appendix 02 : Elapsed Time Assumption

**CONF ALL

This chart is only a proposal. Operators may determine that another way to do the work is more

suitable for them.

DATE: Feb 25/11 SERVICE BULLETIN No.: A340-57-5029

REVISION No.: 00 - Feb 25/11 Page: 1

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Appendix 02 : Elapsed Time Assumption

**CONF ALL

ELAPSED TIME ASSUMPTIONS SERVICE BULLETIN No. A340−57−5029

GET ACCESS (LH SIDE)

MH ET/S

TOTAL MANHOURS

SB ELAPSED TIME

20.0

10.0

STEPS

2.00 2.00

0 10

5.00 5.00

CLOSE−UP (LH SIDE) 3.00 3.00

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

1

1

1

:

:

SB ELAPSED TIME

(HOURS)

2 4 6 8

RADIUS ON THE UPPER

INSPECTION OF THE EXTERNAL

HORIZONTAL CRUCIFORM

FITTING AT FR47 (LH SIDE)

GET ACCESS (RH SIDE) 2.00 2.00

5.00 5.00

CLOSE−UP (RH SIDE) 3.00 3.00

1

1

1

RADIUS ON THE UPPER

INSPECTION OF THE EXTERNAL

HORIZONTAL CRUCIFORM

FITTING AT FR47 (RH SIDE)

F_SB_575029_5_ABAA_01_04

Figure A-FABAA - Sheet 01

Elapsed Time Assumption

DATE: Feb 25/11 SERVICE BULLETIN No.: A340-57-5029

REVISION No.: 00 - Feb 25/11 Page: 2

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REPORTING SHEET

TITLE: WINGS - CENTER WING BOX - INSPECTION OF THE EXTERNAL

RADIUS ON THE UPPER HORIZONTAL CRUCIFORM FITTING AT

FRAME 47

MODIFICATION No.: None

Please complete the appropriate item (A or B):

A - SB WILL BE embodied YES/NO (if NO please comment)

If YES, aircraft concerned (as per SB effectivity by default) and planned dates (month/year) of

embodiment:

B - SB HAS BEEN embodied on aircraft:

Operator comments:

From Airline:

Name/Title:

Signature: Date:

If operational documentation is affected (see Paragraph 1.K of this SB): If information is needed prior to

next normal revision or prior to SB embodiment, please indicate required service(s):

Either: Modification Operational Impact (MOI), if available YES/NO

Or : Intermediate revision YES/NO

Important Information: This SB will only be incorporated in your maintenance and operational

documentation if this sheet is returned to Airbus and signed by a duly authorised representative. With

the next feasible revision, this will result in

- Updating of maintenance documentation to show pre and post SB data.

- Updating of maintenance and operational documentation to show post SB data after embodiment.

If this SB requires previous or simultaneous accomplishment of other SBs, Airbus shall automatically

include them in the manual revisions. Refer to SIL 00-037 for detailed information.

Please return this completed sheet to:

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX FRANCE

Attn: SDC32 Technical Data and Documentation Services

FAX: (+33) 5 61 93 28 06

e-mail: sb.reporting@airbus.com

or via your Resident Customer Support Office.

Alternatively, SB lists via letters or fax are also accepted.

DATE: Feb 25/11 SERVICE BULLETIN No.: A340-57-5029

REVISION No.: 00 - Feb 25/11 Page: 1

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QUALITY PERCEPTION FORM

Use this form to tell us what is your perception of the quality of this Service Bulletin. The reported data

that you provide us will be used to analyse areas of difficulties and to take corrective action to further

improve the quality of our Service Bulletins.

We thank you for the time you have taken in completing this form.

(Please rate on a scale of 1 to 4, with 4 being the highest score)

- Quality rating of this SB 4 3 2 1

- Quality rating of the Accomplishment Instructions 4 3 2 1

- Quality rating of the Illustrations 4 3 2 1

- Is this SB easy to understand ? Y / N

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

short description of the issue.

Planning Material Instructions

X Effectivity X Kit content X Preparation

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

X Manpower X Industry support X Test

X References X Re-identification X Close-Up

X Publication X Tooling X Illustrations

Comments:

Operator: Date:

Name/Title:

Please return this form to:

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX FRANCE

Attn : SEM4 Service Bulletins Management

FAX : (33) 5 61 93 42 51

Or via your Resident Customer Support Office.

DATE: Feb 25/11 SERVICE BULLETIN No.: A340-57-5029

REVISION No.: 00 - Feb 25/11 Page: 1

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