@A330

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 FASTENER HOLES AT

FRAME 40 VERTICAL WEB BELOW INTRADOS

**CONF ALL

MODIFICATIONS

None

REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

During ALI 57.11.04 inspections tasks on the rear fitting of the Frame 40 between stringer 38 & 39

LH/RH side, cracks have been found on the fasteners next to the one to be inspected.

After reaming at second oversize of the subjected hole, the crack is still present.

This Service Bulletin mandates the Inspection of the fasteners holes at Frame 40 Vertical Web between

stringer 38 & 39 - below Intrados, left and right sides for all A330 aircraft pre-modification 44360

embodiment.

The aim of this Inspection Service Bulletin is to implement the corrective inspection necessary to the inservice aircraft.

For aircraft on which FR40 web is already repaired on one side or on both sides as per Repair

Instruction R57115092, Inspection task of this ISB is not necessary for the repaired side(s); dedicated

Repair Design Approval Sheet (RDAS) instructions have to be followed.

For aircraft previously inspected as per Technical Disposition Ref. LR57D11029171 or

LR57D11030741, next inspection is due based on interval value given in this ISB.

Accomplishment of this ISB will permit early detection of cracks on the Frame 40 Vertical Web between

stringer 38 & 39 - below Intrados, left and right sides and will ensure that the structural integrity of the

area is maintained.

The Task ALI 57.11.04 applicable to aircraft pre-mod 44360 will be superseded by accomplishment of

ISB 57-3114.

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114

REVISION No.: 00 - Mar 12/13 Page: 1

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SERVICE BULLETIN

SUMMARY

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 ETOPS AFFECTED NO

STRUCTURAL LIFE EXTN YES VENDOR SB INVOLVED NO

NOTE (1): Service Bulletin must be accomplished.

MATERIAL PRICE INFORMATION

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Kit 573114A01R04 2 17,560.00 Screws, Nuts

EFFECTIVITY

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

BEL BER CPA GIA HDA HFY KAL MAS OHY RSY SAI THA TSC

XAX

This Service Bulletin is only applicable to aircraft on which Mod. No. 44360S13013 and 44360S13482

are not embodied.

CONCURRENT REQUIREMENTS

None

REFERENCES / REPERCUSSIONS

TFU 57.11.00.007

OEB None

AOT None

SIL None

LINE MAINTENANCE AFFECTED No

LIFE LIMIT None

OTHER OIT Ref. 999.0082/12

OTHER OIT Ref. 999.0086/11

NATURE OF THE WORK

AIRCRAFT YES

EQUIPMENT NO

HARD NO

SOFT NO

OBRM NO

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114

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@A330

SERVICE BULLETIN

SUMMARY

MANPOWER

Task 573114-832-801-001: Inspection

TOTAL MANHOURS 37.25

ELAPSED TIME (HOURS) 37.25

Task 573114-833-801-001: Repair

TOTAL MANHOURS 49.25

ELAPSED TIME (HOURS) 49.25

APPENDICES

Appendix 01 : Inspection Report

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114

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@A330

SERVICE BULLETIN

SUMMARY

**CONF ALL

FR40

LH SIDE SHOWN

RH SIDE SYMMETRICAL NOTE:

HOLES OF AREA A TO BE INSPECTED

HOLE OF AREA B TO BE INSPECTED VIEW LOOKING AFT

FR47

FR40

A Z141 Z142 − 

A

B

STGR38

STGR39

STGR40

B

B

CENTER WING BOX LOWER PANEL REFERENCE

G_SB_573114_5_SAAA_01_02

Figure A-FSAAA - Sheet 01

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114

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@A330

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 FASTENER HOLES AT

FRAME 40 VERTICAL WEB BELOW INTRADOS

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

NOTE: This Service Bulletin is only applicable to aircraft on which Mod. No.

44360S13013 and 44360S13482 are not embodied.

(1) Models

330-301 330-321 330-322 330-341 330-342

(2) Effectivity by MSN

0012 0017 0030 0037 0045 0050 0054-0055 0060 0062 0064-0067 0069-0073 0077

0082-0083 0086-0087 0095-0096 0098-0100 0102 0106-0107 0109-0113 0116

0118-0122 0127 0132 0138 0140 0143-0144 0148 0153 0155 0162 0165 0171-0172

(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.

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114

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@A330

SERVICE BULLETIN

OPERATOR MSN

BEL 0030 0037 0045 0082 0095

BER 0127

CPA 0012 0017 0102 0113 0118 0121 0155

GIA 0138 0140 0144 0148 0153 0165

HDA 0071 0083 0099 0106 0109

HFY 0096

KAL 0162 0172

MAS 0067 0069 0073 0077 0100 0107 0110 0116 0119

OHY 0072 0087 0098 0143

RSY 0120 0171

SAI 0055 0070 0086

THA 0050 0060 0062 0064 0065 0066 0112 0122

TSC 0111 0132

XAX 0054

(4) Configuration by MSN

MSN CONFIGURATION

0012 0017 0030 0037 0045 0050 0054 0055 0060 0062 0064

0065 0066 0067 0069 0070 0071 0072 0073 0077 0082 0083

0086 0087 0095 0096 0098 0099 0100 0102 0106 0107 0109

0110 0111 0112 0113 0116 0118 0119 0120 0121 0122 0127

0132 0138 0140 0143 0144 0148 0153 0155 0162 0165 0171

0172

001

(5) Configuration definition

**CONF 001

Config. 001 is valid for all the aircraft given in the effectivity of this Service Bulletin as a

standard configuration.

(6) Material Effectivity

MATERIAL QTY PER A/C SEE NOTES

Kit 573114A01R04 2

Consumable CMLA01 1

B. CONCURRENT REQUIREMENTS

None

C. REASON

(1) History

During ALI 57.11.04 inspections tasks on the rear fitting of the Frame 40 between

stringer 38 & 39 LH/RH side, cracks have been found on the fasteners next to the one

to be inspected.

After reaming at second oversize of the subjected hole, the crack is still present.

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114

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SERVICE BULLETIN

(2) Objective/Action

This Service Bulletin mandates the Inspection of the fasteners holes at Frame 40

Vertical Web between stringer 38 & 39 - below Intrados, left and right sides for all A330

aircraft pre-modification 44360 embodiment.

The aim of this Inspection Service Bulletin is to implement the corrective inspection

necessary to the in-service aircraft.

For aircraft on which FR40 web is already repaired on one side or on both sides as per

Repair Instruction R57115092, Inspection task of this ISB is not necessary for the

repaired side(s); dedicated Repair Design Approval Sheet (RDAS) instructions have to

be followed.

For aircraft previously inspected as per Technical Disposition Ref. LR57D11029171 or

LR57D11030741, next inspection is due based on interval value given in this ISB.

(3) Advantages

Accomplishment of this ISB will permit early detection of cracks on the Frame 40 Vertical

Web between stringer 38 & 39 - below Intrados, left and right sides and will ensure that

the structural integrity of the area is maintained.

(4) Operational/Maintenance Consequences

The Task ALI 57.11.04 applicable to aircraft pre-mod 44360 will be superseded by

accomplishment of ISB 57-3114.

D. DESCRIPTION

To accomplish this Service Bulletin it is necessary to :

Task 573114-832-801-001: Inspection

(1) Do a Special Detailed Inspection of the Fasteners Holes of the Area A at FR40, LH

side

(2) Do a Special Detailed Inspection of the Fasteners Holes of the Area A at FR40, RH

side

(3) Do a Special Detailed Inspection of the Fastener Hole of the Area B at FR40, LH

side

(4) Do a Special Detailed Inspection of the Fastener Hole of the Area B at FR40, RH

side

(5) Do a Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Holes of the

Area A of the Frame 40, LH side

(6) Do a Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Holes of the

Area A of the Frame 40, RH side

(7) Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Holes of the

Area A of the Frame 40, LH side

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114

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SERVICE BULLETIN

(8) Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Holes of the

Area A of the Frame 40, RH side

(9) Do a Rototest Inspection of the Hole of the Area B of the frame 40, LH side

(10) Do a Rototest Inspection of the Hole of the Area B of the frame 40, RH side

Task 573114-833-801-001: Repair

(1) Install new same fasteners pre Service Bulletin No. A330-57-3083 of the Area A in

transition fit, LH side

(2) Install new same fasteners pre Service Bulletin No. A330-57-3083 of the Area A in

transition fit, RH side

(3) Install new same fasteners post Service Bulletin No. A330-57-3083 of the area A in

transition fit, LH side

(4) Install new same fasteners post Service Bulletin No. A330-57-3083 of the area A in

transition fit, RH side

(5) Install new same fastener of the Area B in transition fit, LH side

(6) Install new same fastener of the Area B in transition fit, RH side

(7) Oversize the holes to the first Oversize in comparison with the current hole diameter

of the Area A pre Service Bulletin No. A330-57-3083, LH side

(8) Oversize the holes to the first Oversize in comparison with the current hole diameter

of the Area A pre Service Bulletin No. A330-57-3083, RH side

(9) Oversize the holes to the first Oversize in comparison with the current hole diameter

of the Area A post Service Bulletin No. A330-57-3083, LH side

(10) Oversize the holes to the first Oversize in comparison with the current hole diameter

of the Area A post Service Bulletin No. A330-57-3083, RH side

(11) Oversize the hole to the first Oversize in comparison with the current hole diameter

of the Area B, LH side

(12) Oversize the hole to the first Oversize in comparison with the current hole diameter

of the Area B, RH side

(13) Install new fasteners pre Service Bulletin No. A330-57-3083 of the Area A in

transition fit, LH side

(14) Install new fasteners pre Service Bulletin No. A330-57-3083 of the Area A in

transition fit, RH side

(15) Install new fasteners post Service Bulletin No. A330-57-3083 of the Area A in

transition fit, LH side

(16) Install new fasteners post Service Bulletin No. A330-57-3083 of the Area A in

transition fit, RH side

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114

REVISION No.: 00 - Mar 12/13 Page: 4

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SERVICE BULLETIN

(17) Install new fastener of the Area B in transition fit, LH side

(18) Install new fastener of the Area B in transition fit, RH side

E. COMPLIANCE

(1) Classification

MANDATORY: Service Bulletin must be accomplished.

(2) Accomplishment Timescale

Table 1: Special Detailed Inspection of the Fasteners Holes of the Area A of the frame 40, LH and RH

sides

Condition Action Compliance Time

Threshold

(whichever

occurs first)

Grace

period

(whichever

occurs

first)

Repetitive

Interval

ALI 57-11-04

accomplished

Do a Rototest Inspection

Pre SB

No.A330-57-3083 on LH

and RH Sides, refer to

SUBTASK

573114-832-003 001 for

LH Side and to

SUBTASK

573114-832-008 001 for

RH Side

Refer to table 3

OR

Apply Service Bulletin

No. A330-57-3083

and

Before next flight

ALI 57-11-04 not

accomplished

Pre Service

Bulletin No.

A330-57-3083

Do a Rototest Inspection

Post SB

No.A330-57-3083 on LH

and RH Sides, refer to

SUBTASK

573114-832-004 001 for

LH Side and to

SUBTASK

573114-832-009 001 for

RH Side

Refer to table 4

Perform this rototest at the Threshold

from SB No.A330-57-3083

embodiment

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114

REVISION No.: 00 - Mar 12/13 Page: 5

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SERVICE BULLETIN

Table 1: Special Detailed Inspection of the Fasteners Holes of the Area A of the frame 40, LH and RH

sides

Condition Action Compliance Time

Threshold

(whichever

occurs first)

Grace

period

(whichever

occurs

first)

Repetitive

Interval

ALI 57-11-04

accomplished

ALI 57-11-04 not

accomplished

Post Service

Bulletin No.

A330-57-3083

Do a Rototest Inspection

Post SB

No.A330-57-3083 on LH

and RH Sides, refer to

SUBTASK

573114-832-004 001 for

LH Side and to

SUBTASK

573114-832-009 001 for

RH Side

Refer to table 4

Perform this rototest at the Threshold

from SB No.A330-57-3083

embodiment

Table 2: Special Detailed Inspection of the Fastener Hole of the Area B of the frame 40, LH and RH

sides

Condition Action Compliance Time

Threshold

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive Interval

Config. 001 Do a Rototest Inspection

on LH and RH Sides,

refer to SUBTASK

573114-832-005 001 for

LH Side and to SUBTASK

573114-832-010 001 for

RH Side

Refer to table 5

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114

REVISION No.: 00 - Mar 12/13 Page: 6

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SERVICE BULLETIN

Table 3: Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Fasteners Holes of the

Area A of the frame 40, LH and RH sides

Condition Action Compliance Time

Threshold

from first

flight

(whichever

occurs first)

Grace

period

(whichever

occurs first)

Repetitive

Interval

ALI 57-11-04

accomplished

None None FC optimized

set: 7,400 FC

/24,300 FH

from ALI

embodiment

or

FH optimized

set: 5,950 FC

/40,400 FH

from ALI

embodiment

See NOTE (*)

Pre Service

Bulletin No.

A330-57-3083

ALI 57-11-04

not

accomplished

Do a Rototest Inspection

Pre SB No.A330-57-3083

on LH and RH Sides,

refer to SUBTASK

573114-832-003 001 for

LH Side and to

SUBTASK

573114-832-008 001 for

RH Side

FC optimized

set: 17,400

FC /57,000

FH

or

FH optimized

set: 13,500

FC /91,500

FH

See NOTE (*)

2,400 FC

or 24

months

from SB

issuance

date

None

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114

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SERVICE BULLETIN

Table 3: Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Fasteners Holes of the

Area A of the frame 40, LH and RH sides

Condition Action Compliance Time

Threshold

from first

flight

(whichever

occurs first)

Grace

period

(whichever

occurs first)

Repetitive

Interval

Install New same

fasteners in transition fit

Pre SB No.A330-57-3083

on LH and/or RH Sides,

refer to SUBTASK

573114-833-001 001 for

LH Side and/or to

SUBTASK

573114-833-012 001 for

RH Side

and

Before next

flight

None None

Repeat the Rototest

Inspection of the holes

Pre SB No.

A330-57-3083 on LH

and/or RH Sides, refer to

SUBTASK

573114-832-003 001 for

LH Side and/or to

SUBTASK

573114-832-008 001 for

RH Side

None None FC optimized

set: 7,400 FC

/24,300 FH

or

FH optimized

set: 5,950 FC

/40,400 FH

See NOTE (*)

No Crack found

OR

Apply Service Bulletin

No. A330-57-3083

and

Before next

flight

No Crack found None None

Do a Rototest Inspection

Post SB

No.A330-57-3083 on LH

and RH Sides, refer to

SUBTASK

573114-832-004 001 for

LH Side and to

SUBTASK

573114-832-009 001 for

RH Side

Refer to table 4

Perform this rototest at the Threshold from

SB No.A330-57-3083 embodiment

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114

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SERVICE BULLETIN

Table 3: Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Fasteners Holes of the

Area A of the frame 40, LH and RH sides

Condition Action Compliance Time

Threshold

from first

flight

(whichever

occurs first)

Grace

period

(whichever

occurs first)

Repetitive

Interval

Crack found Oversize the holes to first

oversize in comparison

with the current hole

diameter Pre SB

No.A330-57-3083 on LH

and/or RH Sides, refer to

SUBTASK

573114-833-003 001 for

LH Side and/or to

SUBTASK

573114-833-015 001 for

RH Side

and

Do a Rototest Inspection

Before next

flight

None None

Crack found after Rototest

Inspection

Contact Airbus Before next

flight

None None

Install new fasteners in

transition fit Pre SB

No.A330-57-3083 on LH

and/or RH Sides, refer to

SUBTASK

573114-833-005 001 for

LH Side and/or to

SUBTASK

573114-833-018 001 for

RH Side

and

Before next

flight

No Crack found after Rototest None None

Inspection

Repeat the Rototest

Inspection of the holes

Pre SB No.

A330-57-3083 on LH

and/or RH Sides, refer to

SUBTASK

573114-832-003 001 for

LH Side and/or to

SUBTASK

573114-832-008 001 for

RH Side

None None FC optimized

set: 7,400 FC

/24,300 FH

or

FH optimized

set: 5,950 FC

/40,400 FH

See NOTE (*)

NOTE (*): For FH and FC optimization on A330/A340 aircraft, operators shall select the set that better

suits aircraft operation and utilization (Refer to OIT 999.0086/11).

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114

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SERVICE BULLETIN

Table 4: Rototest Inspection Post Service Bulletin No. A330-57-3083 of the fasteners holes of the

Area A of the frame 40, LH and RH Sides

Condition Action Compliance Time

Threshold from

SB 57-3083

embodiment

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

Post Service Bulletin No.

A330-57-3083

ALI 57-11-04 accomplished or

not

Do a Rototest

Inspection Post SB

No.A330-57-3083 on

LH and RH Sides,

refer to SUBTASK

573114-832-004 001

for LH Side and to

SUBTASK

573114-832-009 001

for RH Side

FC optimized

set: 30,900

FC/100,900 FH

or

FH optimized

set: 23,900 FC

/162,000 FH

See NOTE (*)

2,400 FC or

24 months

from SB

issuance

date

None

Install new same

fasteners in

transition fit Post SB

No.A330-57-3083 on

LH and/or RH Sides,

refer to SUBTASK

573114-833-007 001

for LH Side and/or

to SUBTASK

573114-833-013 001

for RH Side

and

Before next

flight

No crack found None None

Repeat the Rototest

Inspection of the

holes Post SB No.

A330-57-3083 on LH

and/or RH Sides,

refer to SUBTASK

573114-832-004 001

for LH Side and/or

to SUBTASK

573114-832-009 001

for RH Side

None None FC optimized

set: 7,400 FC

/24,300 FH

or

FH optimized

set: 5,950 FC

/40,400 FH

See NOTE (*)

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114

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SERVICE BULLETIN

Table 4: Rototest Inspection Post Service Bulletin No. A330-57-3083 of the fasteners holes of the

Area A of the frame 40, LH and RH Sides

Condition Action Compliance Time

Threshold from

SB 57-3083

embodiment

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

Crack found Oversize the holes

to first oversize in

comparison with the

current hole

diameter on LH

and/or RH Sides,

refer to SUBTASK

573114-833-011 001

for LH Side and/or

to SUBTASK

573114-833-016 001

for RH Side

and

Do a Rototest

Inspection

Before next

flight

None None

Crack found after Rototest

Inspection

Contact Airbus Before next

flight

None None

Install new fasteners

in transition fit Post

SB

No.A330-57-3083 on

LH and/or RH Sides,

refer to SUBTASK

573114-833-009 001

for LH Side and/or

to SUBTASK

573114-833-019 001

for RH Side

and

Before next

flight

No Crack found after Rototest None None

Inspection

Repeat the Rototest

Inspection of the

holes Post SB No.

A330-57-3083 on LH

and/or RH Sides,

refer to SUBTASK

573114-832-004 001

for LH Side and/or

to SUBTASK

573114-832-009 001

for RH Side

None None FC optimized

set: 7,400 FC

/24,300 FH

or

FH optimized

set: 5,950 FC

/40,400 FH

See NOTE (*)

NOTE (*): For FH and FC optimization on A330/A340 aircraft, operators shall select the set that better

suits aircraft operation and utilization (Refer to OIT 999.0086/11).

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114

REVISION No.: 00 - Mar 12/13 Page: 11

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SERVICE BULLETIN

Table 5: Rototest Inspection of the fastener hole of the Area B of the frame 40, LH and RH Sides

Condition Action Compliance Time

Threshold from

first flight

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

Config. 001 Do a Rototest Inspection on

LH and RH Sides, refer to

SUBTASK 573114-832-005

001 for LH Side and to

SUBTASK 573114-832-010

001 for RH Side

FC optimized set:

17,400 FC

/57,000 FH

or

FH optimized set:

13,500 FC

/91,500 FH

See NOTE (*)

2,400 FC or

24 months

from SB

issuance date

None

Install new same fastener in

transition fit on LH and/or

RH Sides, refer to

SUBTASK 573114-833-002

001 for LH Side and/or to

SUBTASK 573114-833-014

001 for RH Side

and

No Crack found Before next flight None None

Repeat the Rototest

Inspection on LH and/or RH

Sides, refer to SUBTASK

573114-832-005 001 for LH

Side and/or to SUBTASK

573114-832-010 001 for RH

Side

None None FC optimized

set: 7,400 FC

/24,300 FH

or

FH optimized

set: 5,950 FC

/40,400 FH

See NOTE (*)

Crack found Oversize the hole to first

oversize in comparison with

the current hole diameter on

LH and/or RH Sides, refer

to SUBTASK

573114-833-010 001 for LH

Side and/or to SUBTASK

573114-833-017 001 for RH

Side

and

Do a Rototest Inspection

Before next flight None None

Crack found after

Rototest Inspection

Contact Airbus Before next flight None None

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114

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SERVICE BULLETIN

Table 5: Rototest Inspection of the fastener hole of the Area B of the frame 40, LH and RH Sides

Condition Action Compliance Time

Threshold from

first flight

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

Install new fastener in

transition fit on LH and/or

RH Sides, refer to

SUBTASK 573114-833-006

001 for LH Side and/or to

SUBTASK 573114-833-020

001 for RH Side

and

No Crack found Before next flight None None

after Rototest

Inspection

Repeat the Rototest

Inspection of the holes on

LH and/or RH Sides, refer

to SUBTASK

573114-832-005 001 for LH

Side and/or to SUBTASK

573114-832-010 001 for RH

Side

None None FC optimized

set: 7,400 FC

/24,300 FH

or

FH optimized

set: 5,950 FC

/40,400 FH

See NOTE (*)

NOTE (*): For FH and FC optimization on A330/A340 aircraft, operators shall select the set that better

suits aircraft operation and utilization (Refer to OIT 999.0086/11).

This Service Bulletin has been classified Mandatory. It is expected that an Airworthiness

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

to confirm this classification. It is anticipated that the AD will confirm the thresholds and

intervals given above but reference should be made to the AD for confirmation of the

mandated accomplishment timescale.

F. APPROVAL

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.

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114

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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.

Task 573114-832-801-001: Inspection

Get Access 13.00

On Aircraft

Do a Special Detailed Inspection of the Fasteners

Holes of the Area A at FR40, LH side

0.25

Do a Special Detailed Inspection of the Fasteners

Holes of the Area A at FR40, RH side

0.25

Do a Special Detailed Inspection of the Fastener Hole

of the Area B at FR40, LH side

0.25

Do a Special Detailed Inspection of the Fastener Hole

of the Area B at FR40, RH side

0.25

Do a Rototest Inspection Pre Service Bulletin No.

A330-57-3083 of the Holes of the Area A of the Frame

40, LH side

2.25

Do a Rototest Inspection Pre Service Bulletin No.

A330-57-3083 of the Holes of the Area A of the Frame

40, RH side

2.25

Do a Rototest Inspection Post Service Bulletin No.

A330-57-3083 of the Holes of the Area A of the Frame

40, LH side

2.25

Do a Rototest Inspection Post Service Bulletin No.

A330-57-3083 of the Holes of the Area A of the Frame

40, RH side

2.25

Do a Rototest Inspection of the Hole of the Area B of

the frame 40, LH side

0.25

Do a Rototest Inspection of the Hole of the Area B of

the frame 40, RH side

0.25

Tests 0.75

Close-Up 13.00

TOTAL MANHOURS 37.25

ELAPSED TIME (HOURS) 37.25

NOTE: For Area A, if Service Bulletin No.A330-57-3083 is accomplished, only the

manhours stating post Service Bulletin No.A330-57-3083 apply.

For Area A, if Service Bulletin No.A330-57-3083 is not accomplished, only the

manhours stating pre Service Bulletin No.A330-57-3083 apply.

NOTE: The minimum manhours necessary to accomplish this Service Bulletin are

those for the Inspection. Depending on the inspection result, additional

manhours can apply.

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114

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SERVICE BULLETIN

Task 573114-833-801-001: Repair

Get Access 13.00

On Aircraft

Install new same fasteners pre Service Bulletin No.

A330-57-3083 of the Area A in transition fit, LH side

1.75

Install new same fasteners pre Service Bulletin No.

A330-57-3083 of the Area A in transition fit, RH side

1.75

Install new same fasteners post Service Bulletin No.

A330-57-3083 of the area A in transition fit, LH side

1.75

Install new same fasteners post Service Bulletin No.

A330-57-3083 of the area A in transition fit, RH side

1.75

Install new same fastener of the Area B in transition fit,

LH side

0.25

Install new same fastener of the Area B in transition fit,

RH side

0.25

Oversize the holes to the first Oversize in comparison

with the current hole diameter of the Area A pre

Service Bulletin No. A330-57-3083, LH side

1.75

Oversize the holes to the first Oversize in comparison

with the current hole diameter of the Area A pre

Service Bulletin No. A330-57-3083, RH side

1.75

Oversize the holes to the first Oversize in comparison

with the current hole diameter of the Area A post

Service Bulletin No. A330-57-3083, LH side

1.75

Oversize the holes to the first Oversize in comparison

with the current hole diameter of the Area A post

Service Bulletin No. A330-57-3083, RH side

1.75

Oversize the hole to the first Oversize in comparison

with the current hole diameter of the Area B, LH side

0.25

Oversize the hole to the first Oversize in comparison

with the current hole diameter of the Area B, RH side

0.25

Install new fasteners pre Service Bulletin No.

A330-57-3083 of the Area A in transition fit, LH side

1.75

Install new fasteners pre Service Bulletin No.

A330-57-3083 of the Area A in transition fit, RH side

1.75

Install new fasteners post Service Bulletin No.

A330-57-3083 of the Area A in transition fit, LH side

1.75

Install new fasteners post Service Bulletin No.

A330-57-3083 of the Area A in transition fit, RH side

1.75

Install new fastener of the Area B in transition fit, LH

side

0.25

Install new fastener of the Area B in transition fit, RH

side

0.25

Tests 0.75

Close-Up 13.00

TOTAL MANHOURS 49.25

ELAPSED TIME (HOURS) 49.25

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SERVICE BULLETIN

NOTE: For Area A, if SB No.A330-57-3083 is accomplished, only the manhours

stating post SB No.A330-57-3083 apply.

For Area A, if SB No.A330-57-3083 is not accomplished, only the manhours

stating pre SB No.A330-57-3083 apply.

H. WEIGHT AND BALANCE

Not Changed

I. ELECTRICAL LOAD DATA

Not Changed

J. REFERENCES

ALI 57.11.04

Aircraft Maintenance Manual (AMM) 06-31-53 06-41-53 12-34-24

20-21-11 21-20-00 21-52-41

25-52-00 25-80-00 36-22-19

52-30-00 53-35-13

Consumable Material List (CML)

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

Non Destructive Test Manual (NTM) 51-10-01

Service Bulletin (SB) A330-57-3083

Standards Manual (SM)

Structural Repair Manual (SRM) 51-11-00 51-22-00 51-24-00

51-42-00 51-43-00 51-44-00

K. PUBLICATION AFFECTED

Airworthiness Limitation Section (ALS) Airworthiness Limitation Section

(ALS) PART 2.

Maintenance Planning Document (MPD) Impact on Scheduled Maintenance:

Refer to MPD

L. INTERCHANGEABILITY/MIXABILITY

Not Applicable

M. SPARES

None

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114

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SERVICE BULLETIN

2. MATERIAL INFORMATION

**CONF ALL

A. MATERIAL - PRICE AND AVAILABILITY

(1) Procurement Addresses

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:

Kit 573114A01R04 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 2590

For ordering by E-mail: airbus.kit@airbus.com

(2) Price and Availability

Kit 573114A01R04

Cost 8,780.00 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.

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

at the issue date of the Service Bulletin. The latest valid price and lead time for ordering

purposes shall be obtained through the AirbusSpares portal or through a request for

quotation to airbus.kit@airbus.com.

B. INDUSTRY SUPPORT INFORMATION

This Service Bulletin is subject to a specific support provided by AIRBUS. For more details

regarding the applicable commercial policy, please contact your Customer Support Director.

C. LIST OF COMPONENTS

Kit 573114A01R04

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

NOTES

1 EN6115V5-12 1 SCREW

2 ASNA2529-5 7 NUT

3 EN6115T7-18 1 SCREW

4 ASNA2531-7 1 NUT

5 EN6115V4-6 4 SCREW

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SERVICE BULLETIN

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

NOTES

6 EN6115V4-10 2 SCREW

7 ASNA2529-4 6 NUT

10 EN6115V5X12 1 SCREW

11 EN6115T7X18 1 SCREW

12 EN6115V4X6 4 SCREW

13 EN6115V4X10 2 SCREW

16 EN6115V6-12 1 SCREW

17 ASNA2529-6 1 NUT

18 EN6115V5-6 4 SCREW

19 EN6115V5-10 2 SCREW

21 EN6115V6X12 1 BOLT

22 EN6115V5X6 4 SCREW

23 EN6115V5X10 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.

D. LIST OF MATERIALS - OPERATOR SUPPLIED

(1) Consumable Materials

NOTE: To accomplish this Service Bulletin it is necessary to use the expendable

parts listed in the AMM Task 21-52-41-000-801 mentioned in paragraph

job set-up and in the AMM Task 21-52-41-400-801 mentioned in

paragraph close-up.

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO CML

MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

Adhesion Promoter For Polysulfide

Sealant

09-028 As required

Polysulphide Fuel Tank Sealant 09-046 As required

Trichloroethane (Methyl Chloroform) 11-004 As required

Lint-Free Cotton Cloth 19-003 As required

(2) Components

None

(3) Equipment

None

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SERVICE BULLETIN

E. PARTS TO BE RE-IDENTIFIED BY OPERATOR

None

F. TOOLING

(1) Tooling - Price and Availability

None

(2) Tools

NOTE: To accomplish this Service Bulletin it is necessary to use the tools listed

in the AMM Task 21-52-41-000-801 mentioned in paragraph job set-up

and in the AMM Task 21-52-41-400-801 mentioned in paragraph closeup.

(3) Special Tools

None

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114

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This Page Intentionally Left Blank

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SERVICE BULLETIN

3. ACCOMPLISHMENT INSTRUCTIONS

Task 573114-832-801-001 - Inspection

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

INCLUDED IN THE REFERENCED PROCEDURES.

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 GROUND SAFETY-LOCKS ARE CORRECTLY

INSTALLED ON THE LANDING GEAR. THIS PREVENTS UNWANTED

MOVEMENT OF THE LANDING GEAR.

CAUTION: ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP

ELECTRICAL WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY

AND MECHANICALLY SERVICEABLE). WHEN YOU DO MAINTENANCE

WORK, REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING,

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

THIS:

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

NECESSARY ON WIRING AND COMPONENTS.

- REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND

OTHER CONTAMINATION.

THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION

AND DAMAGE TO THE ELECTRICAL WIRING INSTALLATION.

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

Task Associated Data

Zone

137 138

Manpower

TOTAL MANHOURS 37.25

ELAPSED TIME (HOURS) 37.25

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SERVICE BULLETIN

A. GENERAL

CAUTION: To accomplish this Service Bulletin it is not necessary to put the aircraft

under zero stress jacking. No zero stress jacking is required also in case of

concurrent accomplishment of maintenance tasks or SBs in frame 40 area.

However this is applicable only for the accomplishment of these tasks/SBs

without deviation. Indeed, in case of heavy repair, a temporary re-installation

of fasteners and/or zero stress jacking procedure could be anticipated.

NOTE: The minimum manhours necessary to accomplish this Service Bulletin are

those for the Inspection. Depending on the inspection result, additional

manhours can apply.

NOTE: The purpose of flow charts are for information only to show the various

Inspection/Repair phases described in this Service Bulletin.

(1) Subtask 573114-910-001-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-31-53

06-41-53

Consumable Material List (CML)

Structural Repair Manual (SRM) 51-42-00

(a) For the Frame (FR) identification (Refer to AMM 06-31-53).

(b) For the identification of Access Panels (Refer to AMM 06-41-53).

(c) For the specification of the material numbers (Mat. No.) refer to Consumable

Material List (CML).

(d) Use a non-metallic spatula to remove the sealant.

(e) In case alternative and substitute fasteners are to be used, you must check that the

associated nut/collar are compatible in accordance with SRM 51-40-00

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

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

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

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

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

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

(2) Subtask 573114-839-001-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

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SERVICE BULLETIN

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

Service Bulletin.

B. PREPARATION

(1) Subtask 573114-941-001-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

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

Task 21-20-00-010-801

Task 25-52-00-000-802

Task 53-35-13-000-802

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

12-34-24-860-802).

(b) Put the access platform(s) in position at door 821.

(2) Subtask 573114-941-002-001 - Safety Precautions

Manpower Resources

Skills NON SPECIFIC

(a) On the AIR control panel 225VU:

1 Make sure that the APU BLEED, the ENG BLEED 1(2) and the PACK 1(2)

pushbutton switches are released.

2 Put a WARNING NOTICE in position to tell persons not to operate these

pushbotton switches.

(b) On the HP ground connectors, put a WARNING NOTICE in position to tell persons

not to supply the ground air source.

(3) Subtask 573114-010-001-001 - Remove/Open for Access in the Belly Fairing Area

RH side

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-010-801

Task 36-22-19-000-801

Task 53-35-13-000-802

Fig. A-FBAAA

Remove/Install the Heat Shield

Sheet 01

Sheet 02

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References

Fig. A-FDBAA

Remove/Install the Air Conditioning

Ducts between FR39.1 and FR40 (Belly

Fairing Area)

Sheet 01

Fig. A-FDCAA

Remove/Install the Air Conditioning

Ducts between FR39.1 and FR40 (Belly

Fairing Area)

Sheet 01

(a) Remove the Belly Fairing Access-Panels 193DB (Refer to AMM Task

53-35-13-000-802).

(b) On the RH side, remove and retain the air-conditioning pack outlet duct as follows

(Refer to AMM Task 21-20-00-010-801 and Fig. A-FDBAA Sheet 01).

1 Remove:

1 Duct Item (26) Retain

(c) On the RH side, remove and retain the air ventilation duct as follows (Refer to

AMM Task 21-20-00-010-801 and Fig. A-FDCAA Sheet 01).

1 Remove:

1 Duct Item (41) Retain

(d) Remove, if necessary, the Wing Bleed-Air Duct Sensing Elements (Refer to AMM

Task 36-22-19-000-801).

(e) Remove the Heat Shield of the RH Conditioning Pack (Refer to Fig. A-FBAAA

Sheet 01 and Fig. A-FBAAA Sheet 02):

1 Heat Shield Item (8) Retain

12 Screw Item (9) Retain

(4) Subtask 573114-010-002-001 - Remove/Open for Access in the Belly Fairing Area

LH side

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 53-35-13-000-802

(a) Remove the Belly Fairing Access-Panels 192PB (Refer to AMM Task

53-35-13-000-802).

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SERVICE BULLETIN

(5) Subtask 573114-941-006-001 - Remove/Open for Access in the FWD CargoCompartment

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-010-801

Task 25-52-00-000-801

Task 25-80-00-000-801

Task 52-30-00-010-801

Fig. A-FDAAA

Remove/Install the Air Conditioning

Ducts between FR39.1 and FR40 (FWD

Cargo-Compartment)

Sheet 01

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE.

(a) Open the FWD cargo-compartment door 821 (Refer to AMM Task

52-30-00-010-801).

(b) Remove the partition panels 131CX, 131DX, 132CX and 132DX (Refer to AMM

Task 25-52-00-000-801).

(c) On the LH and RH sides, remove the air conditioning ducts between Frame 39.1

and Frame 40 (Refer to AMM Task 21-20-00-010-801 and Fig. A-FDAAA Sheet

01).

1 Remove:

2 Duct Item (11) Retain

2 Duct Item (12) Retain

2 Recirculation filterhousingItem (13) Retain

2 Recirculation fan Item (14) Retain

(d) Remove the insulation blankets if necessary (Refer to AMM Task

25-80-00-000-801).

(6) Subtask 573114-110-001-001 - Cleaning of the structure

Manpower Resources

Skills NON SPECIFIC

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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

Trichloroethane (Methyl

Chloroform)

11-004

Lint-Free Cotton Cloth 19-003 As required

WARNING: USE SOLVENTS/CLEANING AGENTS, SEALANTS AND OTHER

SPECIAL MATERIALS ONLY WITH A GOOD FLOW OF AIR THROUGH

THE WORK AREA.

THESE MATERIALS ARE POISONOUS AND 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.

WARNING: OBEY THE MANUFACTURER’S INSTRUCTIONS WHEN YOU USE

THIS/THESE MATERIAL/S.

USE PROTECTIVE CLOTHING, RUBBER GLOVES, GOGGLES AND A

MASK.

(a) Clean the inspection area with:

Trichloroethane

(Methyl Chloroform)

11-004 As required

and (if necessary)

Lint-Free Cotton

Cloth

19-003 As required

(7) Subtask 573114-210-001-001 - Preparation of the inspection Area

Manpower Resources

Skills NON SPECIFIC

References

Structural Repair Manual (SRM) 51-11-00

51-22-00

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(a) Use a FLASHLIGHT to do this inspection if necessary.

(b) Make sure that the surface of the inspection area is clean and smooth.

(c) Do a visual check of the inspection area for damages or discontinuities.

(d) Make sure that there is no:

1 Corrosion damage:

- If you find corrosion damage, refer to the Structural Repair Manual

for Types, inspection, removal and corrosion protection (Refer to SRM

51-22-00).

2 Other damage (cracks, scratches, stress, marks, dents, bumps, ...):

- If you find this type of damage, refer to the Structural Repair Manual for

damage classification and corrective action (Refer to SRM 51-11-00).

C. PROCEDURE

(1) Subtask 573114-832-001-001 - Do a Special Detailed Inspection of the Fasteners

Holes of the Area A at FR40, LH side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills NON DESTRUCTIVE

TESTING

AIRFRAME

References

Non Destructive Test Manual (NTM) 51-10-01

Service Bulletin (SB) A330-57-3083

Fig. A-FFAAA

Flow Chart

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Refer to Fig. A-FFAAA.

(a) If Service Bulletin No.A330-57-3083 is accomplished:

1 Do SUBTASK 573114-832-004 001 Do a Rototest Inspection Post Service

Bulletin No. A330-57-3083 of the Holes of the Area A of the Frame 40,

LH side at the threshold given in the table 4 of the Planning Information

Paragraph E.(2).

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114

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SERVICE BULLETIN

(b) If Service Bulletin No. A330-57-3083 is not accomplished:

1 Do SUBTASK 573114-832-003 001 Do a Rototest Inspection Pre Service

Bulletin No. A330-57-3083 of the Holes of the Area A of the Frame 40,

LH side at the threshold given in the table 3 of the Planning Information

Paragraph E.(2).

or

Apply Service Bulletin No. A330-57-3083 before next flight.

And do the SUBTASK 573114-832-004 001 Do a Rototest Inspection Post

Service Bulletin No. A330-57-3083 of the Holes of the Area A of the Frame

40, LH side at the threshold given in the table 4 of the Planning Information

Paragraph E.(2).

(2) Subtask 573114-832-006-001 - Do a Special Detailed Inspection of the Fasteners

Holes of the Area A at FR40, RH side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills NON DESTRUCTIVE

TESTING

AIRFRAME

References

Service Bulletin (SB) A330-57-3083

Fig. A-FFAAA

Flow Chart

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Refer to Fig. A-FFAAA.

(a) If Service Bulletin No.A330-57-3083 is accomplished:

1 Do SUBTASK 573114-832-009 001 Do a Rototest Inspection Post Service

Bulletin No. A330-57-3083 of the Holes of the Area A of the Frame 40,

RH side at the threshold given in the table 4 of the Planning Information

Paragraph E.(2).

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114

REVISION No.: 00 - Mar 12/13 Page: 28

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@A330

SERVICE BULLETIN

(b) If Service Bulletin No. A330-57-3083 is not accomplished:

1 Do SUBTASK 573114-832-008 001 Do a Rototest Inspection Pre Service

Bulletin No. A330-57-3083 of the Holes of the Area A of the Frame 40,

RH side at the threshold given in the table 3 of the Planning Information

Paragraph E.(2).

or

Apply Service Bulletin No. A330-57-3083 before next flight.

And do the SUBTASK 573114-832-009 001 Do a Rototest Inspection Post

Service Bulletin No. A330-57-3083 of the Holes of the Area A of the Frame

40, RH side at the threshold given in the table 4 of the Planning Information

Paragraph E.(2).

(3) Subtask 573114-832-002-001 - Do a Special Detailed Inspection of the Fastener

Hole of the Area B at FR40, LH side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills NON SPECIFIC

References

Non Destructive Test Manual (NTM) 51-10-01

Fig. A-FFAAA

Flow Chart

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Refer to Fig. A-FFAAA.

(a) Do SUBTASK 573114-832-005 001 Do a Rototest Inspection of the Hole of the

Area B of the frame 40, LH side at the threshold given in the table 5 of the

Planning Information Paragraph E.(2).

(4) Subtask 573114-832-007-001 - Do a Special Detailed Inspection of the Fastener

Hole of the Area B at FR40, RH side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114

REVISION No.: 00 - Mar 12/13 Page: 29

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@A330

SERVICE BULLETIN

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills NON SPECIFIC

References

Non Destructive Test Manual (NTM) 51-10-01

Fig. A-FFAAA

Flow Chart

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Refer to Fig. A-FFAAA.

(a) Do SUBTASK 573114-832-010 001 Do a Rototest Inspection of the Hole of the

Area B of the frame 40, RH side at the threshold given in the table 5 of the

Planning Information Paragraph E.(2).

(5) Subtask 573114-832-003-001 - Do a Rototest Inspection Pre Service Bulletin No.

A330-57-3083 of the Holes of the Area A of the Frame 40, LH side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 2.25

Minimum number of person 1

Subtask elapsed time 2.25

Skills NON SPECIFIC

References

Non Destructive Test Manual (NTM) 51-10-01

Service Bulletin (SB) A330-57-3083

Fig. A-FCAAA

Remove/Install the fasteners

Sheet 01

Sheet 02

Fig. A-FCBAA

Inspection Area

Sheet 01

Sheet 02

At the Threshold/Interval given in the Planning Information Paragraph E.(2):

NOTE: If ALI 57-11-04 is accomplished, the Interval is to be applied.

If ALI 57-11-04 is not accomplished, the Threshold is to be applied.

(a) Do a rototest inspection pre Service Bulletin No. A330-57-3083 of the area A of the

frame 40, LH side.

- Remove the fasteners from holes H41, H42, H44, and H46, LH side:

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114

REVISION No.: 00 - Mar 12/13 Page: 30

5

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@A330

SERVICE BULLETIN

Refer to Fig. A-FCAAA.

4 Screw Item (5) Discard

4 Nut Item (7) Discard

- Remove the fasteners from holes H45 and H259, LH side:

Refer to Fig. A-FCAAA.

2 Screw Item (6) Discard

2 Nut Item (7) Discard

- Remove the fastener from hole H25, LH side:

Refer to Fig. A-FCAAA.

1 Screw Item (1) Discard

1 Nut Item (2) Discard

- Do a rototest inspection at the holes H25, H41, H42, H44, H45, H46, and

H259, LH side.

Refer to Fig. A-FCBAA

Refer to NTM 51-10-01

1 If no crack is found:

a Do SUBTASK 573114-833-001 001 Install new same fasteners pre

Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH side

before next flight

and

Repeat the rototest inspection as described in SUBTASK

573114-832-003 001 Do a Rototest Inspection Pre Service Bulletin No.

A330-57-3083 of the Holes of the Area A of the Frame 40, LH side at the

interval given in the table 3 of the Planning Information Paragraph E.(2).

or

b Apply Service Bulletin No. A330-57-3083 before next flight.

And do the SUBTASK 573114-832-004 001 Do a Rototest Inspection

Post Service Bulletin No. A330-57-3083 of the Holes of the Area A of the

Frame 40, LH side at the threshold given in the table 4 of the Planning

Information Paragraph E.(2).

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114

REVISION No.: 00 - Mar 12/13 Page: 31

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@A330

SERVICE BULLETIN

2 If crack is found:

a Do SUBTASK 573114-833-003 001 Oversize the holes to the first

Oversize in comparison with the current hole diameter of the Area A pre

Service Bulletin No. A330-57-3083, LH side and check if crack is found

with a rototest inspection before next flight.

<1> If crack is found after the rototest inspection:

<a> Contact Airbus before next flight.

<2> If no crack is found after the rototest inspection:

<a> Do SUBTASK 573114-833-005 001 Install new fasteners pre

Service Bulletin No. A330-57-3083 of the Area A in transition

fit, LH side before next flight

and

Repeat the rototest inspection as described in SUBTASK

573114-832-003 001 Do a Rototest Inspection Pre Service

Bulletin No. A330-57-3083 of the Holes of the Area A of the

Frame 40, LH side at the interval given in the table 3 of the

Planning Information Paragraph E.(2).

(b) For the inspection report, refer to Appendix 01.

(6) Subtask 573114-832-008-001 - Do a Rototest Inspection Pre Service Bulletin No.

A330-57-3083 of the Holes of the Area A of the Frame 40, RH side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 2.25

Minimum number of person 1

Subtask elapsed time 2.25

Skills NON SPECIFIC

References

Non Destructive Test Manual (NTM) 51-10-01

Service Bulletin (SB) A330-57-3083

Fig. A-FCAAA

Remove/Install the fasteners

Sheet 01

Sheet 02

Fig. A-FCBAA

Inspection Area

Sheet 01

Sheet 02

At the Threshold/Interval given in the Planning Information Paragraph E.(2):

NOTE: If ALI 57-11-04 is accomplished, the Interval is to be applied.

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114

REVISION No.: 00 - Mar 12/13 Page: 32

5

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@A330

SERVICE BULLETIN

If ALI 57-11-04 is not accomplished, the Threshold is to be applied.

(a) Do a rototest inspection pre Service Bulletin No. A330-57-3083 of the area A of the

frame 40, RH side.

- Remove the fasteners from holes H41, H42, H44, and H46, RH side:

Refer to Fig. A-FCAAA.

4 Screw Item (5) Discard

4 Nut Item (7) Discard

- Remove the fasteners from holes H45 and H259, RH side:

Refer to Fig. A-FCAAA.

2 Screw Item (6) Discard

2 Nut Item (7) Discard

- Remove the fastener from hole H25, RH side:

Refer to Fig. A-FCAAA.

1 Screw Item (1) Discard

1 Nut Item (2) Discard

- Do a rototest inspection at the holes H25, H41, H42, H44, H45, H46, and

H259, RH side.

Refer to Fig. A-FCBAA

Refer to NTM 51-10-01

1 If no crack is found:

a Do SUBTASK 573114-833-012 001 Install new same fasteners pre

Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH side

before next flight

and

Repeat the rototest inspection as described in SUBTASK

573114-832-008 001 Do a Rototest Inspection Pre Service Bulletin No.

A330-57-3083 of the Holes of the Area A of the Frame 40, RH side at the

interval given in the table 3 of the Planning Information Paragraph E.(2).

or

b Apply Service Bulletin No. A330-57-3083 before next flight.

And do the SUBTASK 573114-832-009 001 Do a Rototest Inspection

Post Service Bulletin No. A330-57-3083 of the Holes of the Area A of the

Frame 40, RH side at the threshold given in the table 4 of the Planning

Information Paragraph E.(2).

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114

REVISION No.: 00 - Mar 12/13 Page: 33

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@A330

SERVICE BULLETIN

2 If crack is found:

a Do SUBTASK 573114-833-015 001 Oversize the holes to the first

Oversize in comparison with the current hole diameter of the Area A pre

Service Bulletin No. A330-57-3083, RH side and check if crack is found

with a rototest inspection before next flight.

<1> If crack is found after the rototest inspection:

<a> Contact Airbus before next flight.

<2> If no crack is found after the rototest inspection:

<a> Do SUBTASK 573114-833-018 001 Install new fasteners pre

Service Bulletin No. A330-57-3083 of the Area A in transition

fit, RH side before next flight

and

Repeat the rototest inspection as described in SUBTASK

573114-832-008 001 Do a Rototest Inspection Pre Service

Bulletin No. A330-57-3083 of the Holes of the Area A of the

Frame 40, RH side at the interval given in the table 3 of the

Planning Information Paragraph E.(2).

(b) For the inspection report, refer to Appendix 01.

(7) Subtask 573114-832-004-001 - Do a Rototest Inspection Post Service Bulletin No.

A330-57-3083 of the Holes of the Area A of the Frame 40, LH side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 2.25

Minimum number of person 1

Subtask elapsed time 2.25

Skills NON SPECIFIC

References

Non Destructive Test Manual (NTM) 51-10-01

Service Bulletin (SB) A330-57-3083

Fig. A-FCBAA

Inspection Area

Sheet 01

Sheet 02

Fig. A-FCCAA

Remove/Install the fasteners post

Service Bulletin No. A330-57-3083

Sheet 01

Sheet 02

At the threshold given in the Planning Information Paragraph E.(2):

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114

REVISION No.: 00 - Mar 12/13 Page: 34

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@A330

SERVICE BULLETIN

NOTE: As Service Bulletin No. A330-57-3083 is applied even if ALI 57-11-04 is

accomplished or not, the Threshold is to be applied.

(a) Do a rototest inspection post Service Bulletin No. A330-57-3083 of the area A of

the frame 40, LH side.

- In the area A, remove the fasteners from holes H41, H42, H44, and H46, LH

side:

Refer to Fig. A-FCCAA.

4 Bolt Item (18) Discard

4 Nut Item (2) Discard

- In the area A, remove the fasteners from holes H45 and H259, LH side:

Refer to Fig. A-FCCAA.

2 Bolt Item (19) Discard

2 Nut Item (2) Discard

- In the area A, remove the fastener from hole H25, LH side:

Refer to Fig. A-FCCAA.

1 Bolt Item (16) Discard

1 Nut Item (17) Discard

- Do a rototest inspection at the holes H25, H41, H42, H44, H45, H46, and

H259, LH side.

Refer to Fig. A-FCBAA

Refer to NTM 51-10-01

1 If no crack is found:

a Do SUBTASK 573114-833-007 001 Install new same fasteners post

Service Bulletin No. A330-57-3083 of the area A in transition fit, LH side

before next flight

and

Repeat the rototest inspection as described in SUBTASK

573114-832-004 001 Do a Rototest Inspection Post Service Bulletin No.

A330-57-3083 of the Holes of the Area A of the Frame 40, LH side at the

interval given in the table 4 of the Planning Information Paragraph E.(2).

b For the inspection report, refer to Appendix 01.

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114

REVISION No.: 00 - Mar 12/13 Page: 35

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@A330

SERVICE BULLETIN

2 If crack is found:

a Do SUBTASK 573114-833-011 001 Oversize the holes to the first

Oversize in comparison with the current hole diameter of the Area A post

Service Bulletin No. A330-57-3083, LH side and check if crack is found

with a rototest inspection before next flight.

<1> If crack is found after the rototest inspection:

<a> Contact Airbus before next flight.

<2> If no crack is found after the rototest inspection:

<a> Do SUBTASK 573114-833-009 001 Install new fasteners post

Service Bulletin No. A330-57-3083 of the Area A in transition

fit, LH side before next flight

and

Repeat the rototest inspection as described in SUBTASK

573114-832-004 001 Do a Rototest Inspection Post Service

Bulletin No. A330-57-3083 of the Holes of the Area A of the

Frame 40, LH side at the interval given in the table 4 of the

Planning Information Paragraph E.(2).

(b) For the inspection report, refer to Appendix 01.

(8) Subtask 573114-832-009-001 - Do a Rototest Inspection Post Service Bulletin No.

A330-57-3083 of the Holes of the Area A of the Frame 40, RH side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 2.25

Minimum number of person 1

Subtask elapsed time 2.25

Skills NON SPECIFIC

References

Non Destructive Test Manual (NTM) 51-10-01

Service Bulletin (SB) A330-57-3083

Fig. A-FCBAA

Inspection Area

Sheet 01

Sheet 02

Fig. A-FCCAA

Remove/Install the fasteners post

Service Bulletin No. A330-57-3083

Sheet 01

Sheet 02

At the threshold given in the Planning Information Paragraph E.(2):

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114

REVISION No.: 00 - Mar 12/13 Page: 36

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@A330

SERVICE BULLETIN

NOTE: As Service Bulletin No. A330-57-3083 is applied even if ALI 57-11-04 is

accomplished or not, the Threshold is to be applied.

(a) Do a rototest inspection post Service Bulletin No. A330-57-3083 of the area A of

the frame 40, RH side.

- In the area A, remove the fasteners from holes H41, H42, H44, and H46, RH

side:

Refer to Fig. A-FCCAA.

4 Bolt Item (18) Discard

4 Nut Item (2) Discard

- In the area A, remove the fasteners from holes H45 and H259, RH side:

Refer to Fig. A-FCCAA.

2 Bolt Item (19) Discard

2 Nut Item (2) Discard

- In the area A, remove the fastener from hole H25, RH side:

Refer to Fig. A-FCCAA.

1 Bolt Item (16) Discard

1 Nut Item (17) Discard

- Do a rototest inspection at the holes H25, H41, H42, H44, H45, H46, and

H259, RH side.

Refer to Fig. A-FCBAA

Refer to NTM 51-10-01

1 If no crack is found:

a Do SUBTASK 573114-833-013 001 Install new same fasteners post

Service Bulletin No. A330-57-3083 of the area A in transition fit, RH side

before next flight

and

Repeat the rototest inspection as described in SUBTASK

573114-832-009 001 Do a Rototest Inspection Post Service Bulletin No.

A330-57-3083 of the Holes of the Area A of the Frame 40, RH side at the

interval given in the table 4 of the Planning Information Paragraph E.(2).

b For the inspection report, refer to Appendix 01.

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114

REVISION No.: 00 - Mar 12/13 Page: 37

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@A330

SERVICE BULLETIN

2 If crack is found:

a Do SUBTASK 573114-833-016 001 Oversize the holes to the first

Oversize in comparison with the current hole diameter of the Area A post

Service Bulletin No. A330-57-3083, RH side and check if crack is found

with a rototest inspection before next flight.

<1> If crack is found after the rototest inspection:

<a> Contact Airbus before next flight.

<2> If no crack is found after the rototest inspection:

<a> Do SUBTASK 573114-833-019 001 Install new fasteners post

Service Bulletin No. A330-57-3083 of the Area A in transition

fit, RH side before next flight

and

Repeat the rototest inspection as described in SUBTASK

573114-832-009 001 Do a Rototest Inspection Post Service

Bulletin No. A330-57-3083 of the Holes of the Area A of the

Frame 40, RH side at the interval given in the table 4 of the

Planning Information Paragraph E.(2).

(b) For the inspection report, refer to Appendix 01.

(9) Subtask 573114-832-005-001 - Do a Rototest Inspection of the Hole of the Area B

of the frame 40, LH side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills NON SPECIFIC

References

Non Destructive Test Manual (NTM) 51-10-01

Fig. A-FCAAA

Remove/Install the fasteners

Sheet 01

Sheet 02

Fig. A-FCBAA

Inspection Area

Sheet 01

Sheet 02

Refer to Fig. A-FCAAA.

At the threshold given in the Planning Information Paragraph E.(2):

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114

REVISION No.: 00 - Mar 12/13 Page: 38

5

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@A330

SERVICE BULLETIN

(a) Do a rototest inspection of the area B of the frame 40, LH side.

- Remove fastener from hole H39, LH side, refer to Fig. A-FCAAA Sheet 02:

1 Bolt Item (3) Discard

1 Nut Item (4) Discard

- Do a rototest inspection at hole H39, LH side.

Refer to Fig. A-FCBAA

Refer to NTM 51-10-01

1 If no crack is found:

a Do SUBTASK 573114-833-002 001 Install new same fastener of the Area

B in transition fit, LH side before next flight

and

Repeat the rototest inspection as described in SUBTASK

573114-832-005 001 Do a Rototest Inspection of the Hole of the Area B

of the frame 40, LH side at the interval given in the table 5 of the

Planning Information Paragraph E.(2).

b For the inspection report, refer to Appendix 01.

2 If crack is found:

a Do SUBTASK 573114-833-010 001 Oversize the hole to the first

Oversize in comparison with the current hole diameter of the Area B, LH

side and check if crack is found with a rototest inspection before next

flight.

<1> If crack is found after the rototest inspection:

<a> Contact Airbus before next flight.

<2> If no crack is found after the rototest inspection:

<a> Do SUBTASK 573114-833-006 001 Install new fastener of the

Area B in transition fit, LH side before next flight

and

Repeat the rototest inspection as described in SUBTASK

573114-832-005 001 Do a Rototest Inspection of the Hole of

the Area B of the frame 40, LH side at the interval given in the

table 5 of the Planning Information Paragraph E.(2).

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114

REVISION No.: 00 - Mar 12/13 Page: 39

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@A330

SERVICE BULLETIN

(10) Subtask 573114-832-010-001 - Do a Rototest Inspection of the Hole of the Area B

of the frame 40, RH side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills NON SPECIFIC

References

Non Destructive Test Manual (NTM) 51-10-01

Fig. A-FCAAA

Remove/Install the fasteners

Sheet 01

Sheet 02

Fig. A-FCBAA

Inspection Area

Sheet 01

Sheet 02

Refer to Fig. A-FCAAA.

At the threshold given in the Planning Information Paragraph E.(2):

(a) Do a rototest inspection of the area B of the frame 40, RH side.

- Remove fastener at hole H39, RH side, refer to Fig. A-FCAAA Sheet 02:

1 Bolt Item (3) Discard

1 Nut Item (4) Discard

- Do a rototest inspection at hole H39, RH side.

Refer to Fig. A-FCBAA

Refer to NTM 51-10-01

1 If no crack is found:

a Do SUBTASK 573114-833-014 001 Install new same fastener of the Area

B in transition fit, RH side before next flight

and

Repeat the rototest inspection as described in SUBTASK

573114-832-010 001 Do a Rototest Inspection of the Hole of the Area B

of the frame 40, RH side at the interval given in the table 5 of the

Planning Information Paragraph E.(2).

b For the inspection report, refer to Appendix 01.

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114

REVISION No.: 00 - Mar 12/13 Page: 40

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@A330

SERVICE BULLETIN

2 If crack is found:

a Do SUBTASK 573114-833-017 001 Oversize the hole to the first

Oversize in comparison with the current hole diameter of the Area B, RH

side and check if crack is found with a rototest inspection before next

flight.

<1> If crack is found after the rototest inspection:

<a> Contact Airbus before next flight.

<2> If no crack is found after the rototest inspection:

<a> Do SUBTASK 573114-833-020 001 Install new fastener of the

Area B in transition fit, RH side before next flight

and

Repeat the rototest inspection as described in SUBTASK

573114-832-010 001 Do a Rototest Inspection of the Hole of

the Area B of the frame 40, RH side at the interval given in the

table 5 of the Planning Information Paragraph E.(2).

D. TEST

(1) Subtask 573114-700-003-001 - Testing

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801

Task 21-52-41-400-801

Task 25-52-00-400-801

Task 36-22-19-400-801

Task 53-35-13-400-802

NOTE: This test procedure is to be accomplished after the installation of the

parts removed for the access refer to SUBTASK 573114-410-001 001

Install/Close Items Removed/Opened for access in the Belly Fairing

Area RH side , SUBTASK 573114-410-002 001 Install/Close Items

Removed/Opened for access in the Belly Fairing Area LH side ,

SUBTASK 573114-942-006 001 Install/Close Items Removed/Opened for

Access in the FWD Cargo-Compartment and SUBTASK 573114-942-001

001 Close-up .

(a) Job Set-up:

1 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Belly Fairing Access-Panels (Refer to AMM Task

53-35-13-400-802).

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114

REVISION No.: 00 - Mar 12/13 Page: 41

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SERVICE BULLETIN

2 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Wing Bleed-air Duct Sensing Elements (Refer to

AMM Task 36-22-19-400-801).

3 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Air Conditioning Pack (Refer to AMM Task

21-52-41-400-801).

4 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Ceiling Panels, the Partition Panels and the

Sidewall Panels in the Forward Cargo Compartment (Refer to AMM Task

25-52-00-400-801).

5 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Air-Conditioning Distribution Ducts (Refer to AMM

Task 21-20-00-410-801).

(b) Procedure:

1 Do test procedure as specified after the Installation of the Wing Bleed-air Duct

Sensing Elements (Refer to AMM Task 36-22-19-400-801).

2 Do test procedure as specified after the Installation of the Installation of the Air

Conditioning Pack (Refer to AMM Task 21-52-41-400-801).

3 Do test procedure as specified after the Installation of the Air-Conditioning

Distribution Ducts (Refer to AMM Task 21-20-00-410-801).

E. CLOSE-UP

(1) Subtask 573114-410-001-001 - Install/Close Items Removed/Opened for access in

the Belly Fairing Area RH side

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

Adhesion Promoter For

Polysulfide Sealant

09-028 As required

Polysulphide Fuel Tank

Sealant

09-046 As required

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801

Task 25-80-00-400-801

Task 36-22-19-400-801

Task 53-35-13-400-802

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114

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References

Fig. A-FBAAA

Remove/Install the Heat Shield

Sheet 01

Sheet 02

Fig. A-FDBAA

Remove/Install the Air Conditioning

Ducts between FR39.1 and FR40 (Belly

Fairing Area)

Sheet 01

Fig. A-FDCAA

Remove/Install the Air Conditioning

Ducts between FR39.1 and FR40 (Belly

Fairing Area)

Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR

CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A

GROUND SOURCE.

HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL.

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE.

NOTE: The parts removed for the access must be installed before the

SUBTASK 573114-700-003 001 Testing .

(a) Put the insulation back in position, (Refer to AMM Task 25-80-00-400-801).

Install the Heat Shield of the RH Conditioning Pack, refer to Fig. A-FBAAA Sheet

01 and Fig. A-FBAAA Sheet 02:

1 Heat shield Item (8) Retained at

removal

12 Screw Item (9) Retained at

removal

- Install screws Item (9) with:

Adhesion Promoter

For Polysulfide

Sealant

09-028 As required

Polysulphide Fuel

Tank Sealant

09-046 As required

on and around the screws.

(b) On the RH side, install the air ventilation duct (Refer to AMM Task

21-20-00-410-801 and Fig. A-FDCAA Sheet 01.

1 Install:

1 Duct Item (41) Retained at

removal

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(c) On the RH side, install the air-conditioning pack outlet duct as follows (Refer to

AMM Task 21-20-00-410-801 and Fig. A-FDBAA Sheet 01).

1 Install:

1 Duct Item (26) Retained at

removal

(d) Install the Wing Bleed-Air Duct Sensing Elements (Refer to AMM Task

36-22-19-400-801).

(e) Install the Belly Fairing Access-Panels 193DB (Refer to AMM Task

53-35-13-400-802).

(2) Subtask 573114-410-002-001 - Install/Close Items Removed/Opened for access in

the Belly Fairing Area LH side

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 53-35-13-400-802

NOTE: The parts removed for the access must be installed before the

SUBTASK 573114-700-003 001 Testing .

(a) Install the Belly Fairing Access-Panels 192PB (Refer to AMM Task

53-35-13-400-802).

(3) Subtask 573114-942-006-001 - Install/Close Items Removed/Opened for Access in

the FWD Cargo-Compartment

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801

Task 25-52-00-400-801

Task 25-80-00-400-801

Task 52-30-00-410-801

Fig. A-FDAAA

Remove/Install the Air Conditioning

Ducts between FR39.1 and FR40 (FWD

Cargo-Compartment)

Sheet 01

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE.

NOTE: The parts removed for the access must be installed before the

SUBTASK 573114-700-003 001 Testing .

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(a) On the LH and RH sides, install the air conditioning ducts between Frame 39.1 and

Frame 40 (Refer to AMM Task 21-20-00-410-801 and Fig. A-FDAAA Sheet 01).

1 Install:

2 Duct Item (11) Retained at

removal

2 Duct Item (12) Retained at

removal

2 Recirculation filterhousingItem (13) Retained at

removal

2 Recirculation fan Item (14) Retain

(b) Install the partition panels 131CX, 131DX, 132CX and 132DX (Refer to AMM Task

25-52-00-400-801).

(c) Put the insulation back in position (Refer to AMM Task 25-80-00-400-801).

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

52-30-00-410-801).

(4) Subtask 573114-942-001-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

(a) Remove all the fixtures, tools, test and support equipment used during this

procedure.

(b) Remove the access platform(s).

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

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114

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This Page Intentionally Left Blank

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Task 573114-833-801-001 - Repair

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

INCLUDED IN THE REFERENCED PROCEDURES.

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 GROUND SAFETY-LOCKS ARE CORRECTLY

INSTALLED ON THE LANDING GEAR.

THIS PREVENTS UNWANTED MOVEMENT OF THE LANDING GEAR.

CAUTION: ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP

ELECTRICAL WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY

AND MECHANICALLY SERVICEABLE). WHEN YOU DO MAINTENANCE

WORK, REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING,

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

THIS:

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

NECESSARY ON WIRING AND COMPONENTS.

- REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND

OTHER CONTAMINATION.

THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION

AND DAMAGE TO THE ELECTRICAL WIRING INSTALLATION.

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

Task Associated Data

Zone

137 138

Manpower

TOTAL MANHOURS 49.25

ELAPSED TIME (HOURS) 49.25

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A. GENERAL

(1) Subtask 573114-910-002-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

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

06-41-53, Page Block 001

20-21-11, Page Block 201

Task 20-21-11-911-801

Consumable Material List (CML)

Structural Repair Manual (SRM) 51-24-00

51-42-00

51-43-00

51-44-00

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

(b) For the identification of Access Panels (Refer to AMM 06-41-53, Page Block 001).

(c) For the specification of the material numbers (Mat. No.) refer to Consumable

Material List (CML).

(d) Use a non-metallic spatula to remove the sealant.

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

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

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

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

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

(f) In case alternative and substitute fasteners are to be used, you must check that the

associated nut/collar are compatible in accordance with SRM 51-40-00

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

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

(i) Torque the standard threaded fasteners (Refer to AMM Task 20-21-11-911-801).

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

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

(2) Subtask 573114-839-002-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

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

Service Bulletin.

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B. PREPARATION

NOTE: This PREPARATION procedure is already done in the INSPECTION task.

(1) Subtask 573114-941-003-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

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

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

12-34-24-860-802).

(b) Put the access platform(s) in position at door 821.

(2) Subtask 573114-941-004-001 - Safety Precautions

Manpower Resources

Skills NON SPECIFIC

(a) On the AIR control panel 225VU:

1 Make sure that the APU BLEED, the ENG BLEED 1(2) and the PACK 1(2)

pushbutton switches are released.

2 Put a WARNING NOTICE in position to tell persons not to operate these

pushbotton switches.

(b) On the HP ground connectors, put a WARNING NOTICE in position to tell persons

not to supply the ground air source.

(3) Subtask 573114-010-003-001 - Remove/Open for Accesss in the Belly Fairing Area

RH side

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-010-801

Task 36-22-19-000-801

Task 53-35-13-000-802

Fig. A-FBAAA

Remove/Install the Heat Shield

Sheet 01

Sheet 02

Fig. A-FDBAA

Remove/Install the Air Conditioning

Ducts between FR39.1 and FR40 (Belly

Fairing Area)

Sheet 01

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References

Fig. A-FDCAA

Remove/Install the Air Conditioning

Ducts between FR39.1 and FR40 (Belly

Fairing Area)

Sheet 01

(a) Remove the Belly Fairing Access-Panels 193DB (Refer to AMM Task

53-35-13-000-802).

(b) On the RH side, remove and retain the air-conditioning pack outlet duct as follows

(Refer to AMM Task 21-20-00-010-801 and Fig. A-FDBAA Sheet 01).

1 Remove:

1 Duct Item (26) Retain

(c) On the RH side, remove and retain the air ventilation duct as follows (Refer to

AMM Task 21-20-00-010-801 and Fig. A-FDCAA Sheet 01).

1 Remove:

1 Duct Item (41) Retain

(d) Remove, if necessary, the Wing Bleed-Air Duct Sensing Elements (Refer to AMM

Task 36-22-19-000-801).

(e) Remove the Heat Shield of the RH Conditioning Pack (Refer to Fig. A-FBAAA

Sheet 01 and Fig. A-FBAAA Sheet 02):

1 Heat Shield Item (8) Retain

12 Screw Item (9) Retain

(4) Subtask 573114-010-004-001 - Remove/Open for Access in the Belly Fairing Area

LH side

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 53-35-13-000-802

(a) Remove of the Belly Fairing Access-Panels 192PB (Refer to AMM Task

53-35-13-000-802).

(5) Subtask 573114-941-005-001 - Remove/Open for Access in the FWD CargoCompartment

Manpower Resources

Skills NON SPECIFIC

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References

Aircraft Maintenance Manual (AMM) Task 21-20-00-010-801

Task 25-52-00-000-801

Task 25-80-00-000-801

Task 52-30-00-010-801

Fig. A-FDAAA

Remove/Install the Air Conditioning

Ducts between FR39.1 and FR40 (FWD

Cargo-Compartment)

Sheet 01

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE.

(a) Open the FWD cargo-compartment door 821 (Refer to AMM Task

52-30-00-010-801).

(b) Remove the partition panels 131CX, 131DX, 132CX and 132DX (Refer to AMM

Task 25-52-00-000-801).

(c) On the LH and RH sides, remove, if necessary, the air conditioning ducts between

Frame 39.1 and Frame 40 (Refer to AMM Task 21-20-00-010-801 and Fig. AFDAAA Sheet 01).

1 Remove:

2 Duct Item (11) Retain

2 Duct Item (12) Retain

2 Recirculation filterhousingItem (13) Retain

2 Recirculation fan Item (14) Retain

(d) Remove the insulation blankets if necessary (Refer to AMM Task

25-80-00-000-801).

(6) Subtask 573114-110-002-001 - Cleaning of the structure

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

Trichloroethane (Methyl

Chloroform)

11-004 As required

Lint-Free Cotton Cloth 19-003 As required

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114

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WARNING: USE SOLVENTS/CLEANING AGENTS, SEALANTS AND OTHER

SPECIAL MATERIALS ONLY WITH A GOOD FLOW OF AIR THROUGH

THE WORK AREA.

THESE MATERIALS ARE POISONOUS AND 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.

WARNING: OBEY THE MANUFACTURER’S INSTRUCTIONS WHEN YOU USE

THIS/THESE MATERIAL/S.

USE PROTECTIVE CLOTHING, RUBBER GLOVES, GOGGLES AND A

MASK.

Clean the inspection area with:

Trichloroethane

(Methyl Chloroform)

11-004 As required

and (if necessary)

Lint-Free Cotton

Cloth

19-003 As required

(7) Subtask 573114-210-002-001 - Preparation of the repair Areas

Manpower Resources

Skills NON SPECIFIC

References

Structural Repair Manual (SRM) 51-11-00

51-22-00

(a) Use a FLASHLIGHT to do this repair if necessary.

(b) Make sure that the surface of the repair area is clean and smooth.

(c) Do a visual check of the repair area for damages or discontinuities.

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(d) Make sure that there is no:

1 Corrosion damage:

- If you find corrosion damage, refer to the Structural Repair Manual

for Types, inspection, removal and corrosion protection (Refer to SRM

51-22-00).

2 Other damage (cracks, scratches, stress, marks, dents, bumps, ...):

- If you find this type of damage, refer to the Structural Repair Manual for

damage classification and corrective action (Refer to SRM 51-11-00).

C. PROCEDURE

(1) Subtask 573114-833-001-001 - Install new same fasteners pre Service Bulletin No.

A330-57-3083 of the Area A in transition fit, LH side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 1.75

Minimum number of person 1

Subtask elapsed time 1.75

Skills AIRFRAME

Material necessary to do the job

Kit 573114A01R04

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 EN6115V5-12 1 SCREW

2 ASNA2529-5 1 NUT

5 EN6115V4-6 4 SCREW

6 EN6115V4-10 2 SCREW

7 ASNA2529-4 6 NUT

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

References

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

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCAAA

Remove/Install the fasteners

Sheet 01

Sheet 02

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Refer to Fig. A-FCAAA Sheet 01 and Fig. A-FCAAA Sheet 02.

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

In accordance with SRM 51-43-00

In accordance with SRM 51-42-00

(a) Depending on inspection results of the Area A, if no crack is found, install the

fasteners.

1 In the area A:

a Install the fasteners at holes H41, H42, H44 and H46:

4 Screw EN6115V4-6 Item 5

4 Nut ASNA2529-4 Item 7

Wet install the fasteners with:

Sealant-Brush

Consistency

09-013 As required

b Install the fastener at hole H25:

1 Screw EN6115V5-12 Item 1

1 Nut ASNA2529-5 Item 2

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

c Install the fasteners at holes H45 and H259:

2 Screw EN6115V4-10 Item 6

2 Nut ASNA2529-4 Item 7

Wet install the fasteners with:

Sealant-Brush

Consistency

09-013 As required

(2) Subtask 573114-833-012-001 - Install new same fasteners pre Service Bulletin No.

A330-57-3083 of the Area A in transition fit, RH side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114

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Manpower Resources

Manhours 1.75

Minimum number of person 1

Subtask elapsed time 1.75

Skills AIRFRAME

Material necessary to do the job

Kit 573114A01R04

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 EN6115V5-12 1 SCREW

2 ASNA2529-5 1 NUT

5 EN6115V4-6 4 SCREW

6 EN6115V4-10 2 SCREW

7 ASNA2529-4 6 NUT

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

References

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

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCAAA

Remove/Install the fasteners

Sheet 01

Sheet 02

Refer to Fig. A-FCAAA Sheet 01 and Fig. A-FCAAA Sheet 02.

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

In accordance with SRM 51-43-00

In accordance with SRM 51-42-00

(a) Depending on inspection results of the Area A, if no crack is found, install the

fasteners.

1 In the area A:

a Install the fasteners at holes H41, H42, H44 and H46:

4 Screw EN6115V4-6 Item 5

4 Nut ASNA2529-4 Item 7

Wet install the fasteners with:

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Sealant-Brush

Consistency

09-013 As required

b Install the fastener at hole H25:

1 Screw EN6115V5-12 Item 1

1 Nut ASNA2529-5 Item 2

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

c Install the fasteners at holes H45 and H259:

2 Screw EN6115V4-10 Item 6

2 Nut ASNA2529-4 Item 7

Wet install the fasteners with:

Sealant-Brush

Consistency

09-013 As required

(3) Subtask 573114-833-007-001 - Install new same fasteners post Service Bulletin No.

A330-57-3083 of the area A in transition fit, LH side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 1.75

Minimum number of person 1

Subtask elapsed time 1.75

Skills AIRFRAME

Material necessary to do the job

Kit 573114A01R04

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

2 ASNA2529-5 6 NUT

16 EN6115V6-12 1 SCREW

17 ASNA2529-6 1 NUT

18 EN6115V5-6 4 SCREW

19 EN6115V5-10 2 SCREW

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Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

References

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

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCCAA

Remove/Install the fasteners post

Service Bulletin No. A330-57-3083

Sheet 01

Sheet 02

Refer to Fig. A-FCCAA Sheet 01and Fig. A-FCCAA Sheet 02.

In accordance with SRM 51-43-00

In accordance with SRM 51-42-00

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

(a) Depending on inspection results of the Area A, if no crack is found, install the

fasteners.

1 In the area A:

a Install the fasteners at holes H41, H42, H44 and H46:

4 Screw EN6115V5-6 Item 18

4 Nut ASNA2529-5 Item 2

Wet install the fasteners with:

Sealant-Brush

Consistency

09-013 As required

b Install the fastener at hole H25:

1 Screw EN6115V6-12 Item 16

1 Nut ASNA2529-6 Item 17

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

c Install the fasteners at holes H45 and H259:

2 Screw EN6115V5-10 Item 19

2 Nut ASNA2529-5 Item 2

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Wet install the fasteners with:

Sealant-Brush

Consistency

09-013 As required

(4) Subtask 573114-833-013-001 - Install new same fasteners post Service Bulletin No.

A330-57-3083 of the area A in transition fit, RH side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 1.75

Minimum number of person 1

Subtask elapsed time 1.75

Skills AIRFRAME

Material necessary to do the job

Kit 573114A01R04

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

2 ASNA2529-5 6 NUT

16 EN6115V6-12 1 SCREW

17 ASNA2529-6 1 NUT

18 EN6115V5-6 4 SCREW

19 EN6115V5-10 2 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

References

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

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCCAA

Remove/Install the fasteners post

Service Bulletin No. A330-57-3083

Sheet 01

Sheet 02

Refer to Fig. A-FCCAA Sheet 01 and Fig. A-FCCAA Sheet 02.

In accordance with SRM 51-43-00

In accordance with SRM 51-42-00

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

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(a) Depending on inspection results of the Area A, if no crack is found, install the

fasteners.

1 In the area A:

a Install the fasteners at holes H41, H42, H44 and H46:

4 Screw EN6115V5-6 Item 18

4 Nut ASNA2529-5 Item 2

Wet install the fasteners with:

Sealant-Brush

Consistency

09-013 As required

b Install the fastener at hole H25:

1 Screw EN6115V6-12 Item 16

1 Nut ASNA2529-6 Item 17

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

c Install the fasteners at holes H45 and H259:

2 Screw EN6115V5-10 Item 19

2 Nut ASNA2529-5 Item 2

Wet install the fasteners with:

Sealant-Brush

Consistency

09-013 As required

(5) Subtask 573114-833-002-001 - Install new same fastener of the Area B in transition

fit, LH side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114

REVISION No.: 00 - Mar 12/13 Page: 59

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SERVICE BULLETIN

Material necessary to do the job

Kit 573114A01R04

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

3 EN6115T7-18 1 SCREW

4 ASNA2531-7 1 NUT

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

References

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

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCAAA

Remove/Install the fasteners

Sheet 01

Sheet 02

Refer to Fig. A-FCAAA Sheet 01 and Fig. A-FCAAA Sheet 02

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

In accordance with SRM 51-42-00

In accordance with SRM 51-43-00

(a) Depending on inspection results of the Area B, if no crack is found, install the

fastener.

1 In the Area B:

a Install the fastener at hole H39:

1 Screw EN6115T7-18 Item 3

1 Nut ASNA2531-7 Item 4

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

(6) Subtask 573114-833-014-001 - Install new same fastener of the Area B in transition

fit, RH side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114

REVISION No.: 00 - Mar 12/13 Page: 60

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@A330

SERVICE BULLETIN

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

Material necessary to do the job

Kit 573114A01R04

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

3 EN6115T7-18 1 SCREW

4 ASNA2531-7 1 NUT

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

References

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

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCAAA

Remove/Install the fasteners

Sheet 01

Sheet 02

Refer to Fig. A-FCAAA Sheet 01 and Fig. A-FCAAA Sheet 02

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

In accordance with SRM 51-42-00

In accordance with SRM 51-43-00

(a) Depending on inspection results of the Area B, if no crack is found, install the

fastener.

1 In the Area B:

a Install the fastener at hole H39:

1 Screw EN6115T7-18 Item 3

1 Nut ASNA2531-7 Item 4

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114

REVISION No.: 00 - Mar 12/13 Page: 61

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@A330

SERVICE BULLETIN

(7) Subtask 573114-833-003-001 - Oversize the holes to the first Oversize in

comparison with the current hole diameter of the Area A pre Service Bulletin No.

A330-57-3083, LH side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 1.75

Minimum number of person 1

Subtask elapsed time 1.75

Skills AIRFRAME

References

Non Destructive Test Manual (NTM) 51-10-01

Structural Repair Manual (SRM) 51-44-00

Fig. A-FCAAA

Remove/Install the fasteners

Sheet 01

Sheet 02

Refer to Fig. A-FCAAA Sheet 02.

In accordance with SRM 51-44-00

(a) Depending on inspection results of the Area A, if crack is found, oversize the holes.

1 In the area A:

a Drill to the first oversize diameter the holes H25, H41, H42, H44, H45,

H46 and H259 to the dimension given in Fig. A-FCAAA Sheet 02.

b Do a rototest inspection on the drilled holes to check if the crack is still

present.

Refer to NTM 51-10-01

(8) Subtask 573114-833-015-001 - Oversize the holes to the first Oversize in

comparison with the current hole diameter of the Area A pre Service Bulletin No.

A330-57-3083, RH side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 1.75

Minimum number of person 1

Subtask elapsed time 1.75

Skills AIRFRAME

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114

REVISION No.: 00 - Mar 12/13 Page: 62

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@A330

SERVICE BULLETIN

References

Non Destructive Test Manual (NTM) 51-10-01

Structural Repair Manual (SRM) 51-44-00

Fig. A-FCAAA

Remove/Install the fasteners

Sheet 01

Sheet 02

Refer to Fig. A-FCAAA Sheet 02.

In accordance with SRM 51-44-00

(a) Depending on inspection results of the Area A, if crack is found, oversize the holes.

1 In the area A:

a Drill to the first oversize diameter the holes H25, H41, H42, H44, H45,

H46 and H259 to the dimension given in Fig. A-FCAAA Sheet 02.

b Do a rototest inspection on the drilled holes to check if the crack is still

present.

Refer to NTM 51-10-01

(9) Subtask 573114-833-011-001 - Oversize the holes to the first Oversize in

comparison with the current hole diameter of the Area A post Service Bulletin No.

A330-57-3083, LH side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 1.75

Minimum number of person 1

Subtask elapsed time 1.75

Skills AIRFRAME

References

Non Destructive Test Manual (NTM) 51-10-01

Structural Repair Manual (SRM) 51-44-00

Fig. A-FCCAA

Remove/Install the fasteners post

Service Bulletin No. A330-57-3083

Sheet 01

Sheet 02

Refer to Fig. A-FCCAA Sheet 02.

In accordance with SRM 51-44-00

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114

REVISION No.: 00 - Mar 12/13 Page: 63

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SERVICE BULLETIN

(a) Depending on inspection results of the Area A, if crack is found, oversize the holes.

1 In the area A:

a Drill to the first oversize diameter the holes H25, H41, H42, H44, H45,

H46 and H259 to the dimension given in Fig. A-FCCAA Sheet 02.

b Do a rototest inspection on the drilled holes to check if the crack is still

present.

Refer to NTM 51-10-01

(10) Subtask 573114-833-016-001 - Oversize the holes to the first Oversize in

comparison with the current hole diameter of the Area A post Service Bulletin No.

A330-57-3083, RH side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 1.75

Minimum number of person 1

Subtask elapsed time 1.75

Skills AIRFRAME

References

Non Destructive Test Manual (NTM) 51-10-01

Structural Repair Manual (SRM) 51-44-00

Fig. A-FCCAA

Remove/Install the fasteners post

Service Bulletin No. A330-57-3083

Sheet 01

Sheet 02

Refer to Fig. A-FCCAA Sheet 02.

In accordance with SRM 51-44-00

(a) Depending on inspection results of the Area A, if crack is found, oversize the holes.

1 In the area A:

a Drill to the first oversize diameter the holes H25, H41, H42, H44, H45,

H46 and H259 to the dimension given in Fig. A-FCCAA Sheet 02.

b Do a rototest inspection on the drilled holes to check if the crack is still

present.

Refer to NTM 51-10-01

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114

REVISION No.: 00 - Mar 12/13 Page: 64

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@A330

SERVICE BULLETIN

(11) Subtask 573114-833-010-001 - Oversize the hole to the first Oversize in

comparison with the current hole diameter of the Area B, LH side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

References

Non Destructive Test Manual (NTM) 51-10-01

Structural Repair Manual (SRM) 51-44-00

Fig. A-FCAAA

Remove/Install the fasteners

Sheet 01

Sheet 02

Refer to Fig. A-FCAAA Sheet 02.

In accordance with SRM 51-44-00

(a) Depending on inspection results of the Area B, if crack is found, oversize the hole.

1 In the Area B:

a Drill to the first oversize diameter the hole H39 to the dimension given in

Fig. A-FCAAA Sheet 02.

b Do a rototest inspection on the drilled hole to check if the crack is still

present.

Refer to NTM 51-10-01

(12) Subtask 573114-833-017-001 - Oversize the hole to the first Oversize in

comparison with the current hole diameter of the Area B, RH side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

References

Non Destructive Test Manual (NTM) 51-10-01

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114

REVISION No.: 00 - Mar 12/13 Page: 65

5

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@A330

SERVICE BULLETIN

References

Structural Repair Manual (SRM) 51-44-00

Fig. A-FCAAA

Remove/Install the fasteners

Sheet 01

Sheet 02

Refer to Fig. A-FCAAA Sheet 02.

In accordance with SRM 51-44-00

(a) Depending on inspection results of the Area B, if crack is found, oversize the hole.

1 In the Area B:

a Drill to the first oversize diameter the hole H39 to the dimension given in

Fig. A-FCAAA Sheet 02.

b Do a rototest inspection on the drilled hole to check if the crack is still

present.

Refer to NTM 51-10-01

(13) Subtask 573114-833-005-001 - Install new fasteners pre Service Bulletin No.

A330-57-3083 of the Area A in transition fit, LH side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 1.75

Minimum number of person 1

Subtask elapsed time 1.75

Skills AIRFRAME

Material necessary to do the job

Kit 573114A01R04

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

2 ASNA2529-5 1 NUT

7 ASNA2529-4 6 NUT

10 EN6115V5X12 1 SCREW

12 EN6115V4X6 4 SCREW

13 EN6115V4X10 2 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114

REVISION No.: 00 - Mar 12/13 Page: 66

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@A330

SERVICE BULLETIN

References

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

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCAAA

Remove/Install the fasteners

Sheet 01

Sheet 02

Refer to Fig. A-FCAAA Sheet 02

In accordance with SRM 51-42-00

In accordance with SRM 51-43-00

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

(a) Depending on inspection results of the Area A, if no crack is found, install the new

fasteners.

1 In the area A:

a Install the fasteners at holes H41, H42, H44 and H46:

4 Screw EN6115V4X6 Item 12

4 Nut ASNA2529-4 Item 7

Wet install the fasteners with:

Sealant-Brush

Consistency

09-013 As required

b Install the fastener at hole H25:

1 Screw EN6115V5X12 Item 10

1 Nut ASNA2529-5 Item 2

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

c Install the fasteners at holes H45 and H259:

2 Screw EN6115V4X10 Item 13

2 Nut ASNA2529-4 Item 7

Wet install the fasteners with:

Sealant-Brush

Consistency

09-013 As required

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114

REVISION No.: 00 - Mar 12/13 Page: 67

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@A330

SERVICE BULLETIN

(14) Subtask 573114-833-018-001 - Install new fasteners pre Service Bulletin No.

A330-57-3083 of the Area A in transition fit, RH side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 1.75

Minimum number of person 1

Subtask elapsed time 1.75

Skills AIRFRAME

Material necessary to do the job

Kit 573114A01R04

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

2 ASNA2529-5 1 NUT

7 ASNA2529-4 6 NUT

10 EN6115V5X12 1 SCREW

12 EN6115V4X6 4 SCREW

13 EN6115V4X10 2 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

References

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

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCAAA

Remove/Install the fasteners

Sheet 01

Sheet 02

Refer to Fig. A-FCAAA Sheet 02

In accordance with SRM 51-42-00

In accordance with SRM 51-43-00

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

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114

REVISION No.: 00 - Mar 12/13 Page: 68

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SERVICE BULLETIN

(a) Depending on inspection results of the Area A, if no crack is found, install the new

fasteners.

1 In the area A:

a Install the fasteners at holes H41, H42, H44 and H46:

4 Screw EN6115V4X6 Item 12

4 Nut ASNA2529-4 Item 7

Wet install the fasteners with:

Sealant-Brush

Consistency

09-013 As required

b Install the fastener at hole H25:

1 Screw EN6115V5X12 Item 10

1 Nut ASNA2529-5 Item 2

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

c Install the fasteners at holes H45 and H259:

2 Screw EN6115V4X10 Item 13

2 Nut ASNA2529-4 Item 7

Wet install the fasteners with:

Sealant-Brush

Consistency

09-013 As required

(15) Subtask 573114-833-009-001 - Install new fasteners post Service Bulletin No.

A330-57-3083 of the Area A in transition fit, LH side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 1.75

Minimum number of person 1

Subtask elapsed time 1.75

Skills AIRFRAME

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114

REVISION No.: 00 - Mar 12/13 Page: 69

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@A330

SERVICE BULLETIN

Material necessary to do the job

Kit 573114A01R04

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

2 ASNA2529-5 6 NUT

17 ASNA2529-6 1 NUT

21 EN6115V6X12 1 BOLT

22 EN6115V5X6 4 SCREW

23 EN6115V5X10 2 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

References

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

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCCAA

Remove/Install the fasteners post

Service Bulletin No. A330-57-3083

Sheet 01

Sheet 02

Refer to Fig. A-FCCAA Sheet 02.

In accordance with SRM 51-43-00

In accordance with SRM 51-42-00

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

(a) Depending on inspection results of the area A, if no crack is found, install the new

fasteners.

1 In the area A:

a Install the fasteners at holes H41, H42, H44 and H46:

4 Screw EN6115V5X6 Item 22

4 Nut ASNA2529-5 Item 2

Wet install the fasteners with:

Sealant-Brush

Consistency

09-013 As required

b Install the fastener at hole H25:

1 Bolt EN6115V6X12 Item 21

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114

REVISION No.: 00 - Mar 12/13 Page: 70

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SERVICE BULLETIN

1 Nut ASNA2529-6 Item 17

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

c Install the fasteners at holes H45 and H259:

2 Screw EN6115V5X10 Item 23

2 Nut ASNA2529-5 Item 2

Wet install the fasteners with:

Sealant-Brush

Consistency

09-013 As required

(16) Subtask 573114-833-019-001 - Install new fasteners post Service Bulletin No.

A330-57-3083 of the Area A in transition fit, RH side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 1.75

Minimum number of person 1

Subtask elapsed time 1.75

Skills AIRFRAME

Material necessary to do the job

Kit 573114A01R04

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

2 ASNA2529-5 6 NUT

17 ASNA2529-6 1 NUT

21 EN6115V6X12 1 BOLT

22 EN6115V5X6 4 SCREW

23 EN6115V5X10 2 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

References

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

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114

REVISION No.: 00 - Mar 12/13 Page: 71

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@A330

SERVICE BULLETIN

References

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCCAA

Remove/Install the fasteners post

Service Bulletin No. A330-57-3083

Sheet 01

Sheet 02

Refer to Fig. A-FCCAA Sheet 02.

In accordance with SRM 51-43-00

In accordance with SRM 51-42-00

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

(a) Depending on inspection results of the area A, if no crack is found, install the new

fasteners.

1 In the area A:

a Install the fasteners at holes H41, H42, H44 and H46:

4 Screw EN6115V5X6 Item 22

4 Nut ASNA2529-5 Item 2

Wet install the fasteners with:

Sealant-Brush

Consistency

09-013 As required

b Install the fastener at hole H25:

1 Bolt EN6115V6X12 Item 21

1 Nut ASNA2529-6 Item 17

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

c Install the fasteners at holes H45 and H259:

2 Screw EN6115V5X10 Item 23

2 Nut ASNA2529-5 Item 2

Wet install the fasteners with:

Sealant-Brush

Consistency

09-013 As required

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114

REVISION No.: 00 - Mar 12/13 Page: 72

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@A330

SERVICE BULLETIN

(17) Subtask 573114-833-006-001 - Install new fastener of the Area B in transition fit,

LH side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

Material necessary to do the job

Kit 573114A01R04

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

4 ASNA2531-7 1 NUT

11 EN6115T7X18 1 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

References

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

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCAAA

Remove/Install the fasteners

Sheet 01

Sheet 02

Refer to Fig. A-FCAAA Sheet 02.

In accordance with SRM 51-43-00

In accordance with SRM 51-42-00

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

(a) Depending on inspection results of the area B, if no crack is found, install the new

fastener.

1 In the Area B:

a Install the fastener at hole H39:

1 Screw EN6115T7X18 Item 11

1 Nut ASNA2531-7 Item 4

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114

REVISION No.: 00 - Mar 12/13 Page: 73

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SERVICE BULLETIN

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

(18) Subtask 573114-833-020-001 - Install new fastener of the Area B in transition fit,

RH side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

Material necessary to do the job

Kit 573114A01R04

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

4 ASNA2531-7 1 NUT

11 EN6115T7X18 1 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

References

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

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCAAA

Remove/Install the fasteners

Sheet 01

Sheet 02

Refer to Fig. A-FCAAA Sheet 02.

In accordance with SRM 51-43-00

In accordance with SRM 51-42-00

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

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114

REVISION No.: 00 - Mar 12/13 Page: 74

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SERVICE BULLETIN

(a) Depending on inspection results of the area B, if no crack is found, install the new

fastener.

1 In the Area B:

a Install the fastener at hole H39:

1 Screw EN6115T7X18 Item 11

1 Nut ASNA2531-7 Item 4

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

D. TEST

(1) Subtask 573114-700-002-001 - Testing

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801

Task 21-52-41-400-801

Task 25-52-00-400-801

Task 36-22-19-400-801

Task 53-35-13-400-802

NOTE: This test procedure is to be accomplished after the installation of the

parts removed for the access refer to SUBTASK 573114-942-002 001

Install/Close Items Removed/Opened for access in the Belly Fairing

Area RH side , SUBTASK 573114-942-003 001 Install/Close Item

Removed/Opened for access in the Belly Fairing Area LH side ,

SUBTASK 573114-942-004 001 Install/Close Items Removed/Opened for

Access in the FWD Cargo-Compartment and SUBTASK 573114-942-005

001 Close-up .

(a) Job Set-up:

1 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Belly Fairing Access-Panels (Refer to AMM Task

53-35-13-400-802).

2 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Wing Bleed-air Duct Sensing Elements (Refer to

AMM Task 36-22-19-400-801).

3 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Air Conditioning Pack (Refer to AMM Task

21-52-41-400-801).

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114

REVISION No.: 00 - Mar 12/13 Page: 75

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SERVICE BULLETIN

4 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Ceiling Panels, the Partition Panels and the

Sidewall Panels in the Forward Cargo Compartment (Refer to AMM Task

25-52-00-400-801).

5 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Air-Conditioning Distribution Ducts (Refer to AMM

Task 21-20-00-410-801).

(b) Procedure:

1 Do test procedure as specified after the Installation of the Wing Bleed-air Duct

Sensing Elements (Refer to AMM Task 36-22-19-400-801).

2 Do test procedure as specified after the Installation of the Installation of the Air

Conditioning Pack (Refer to AMM Task 21-52-41-400-801).

3 Do test procedure as specified after the Installation of the Air-Conditioning

Distribution Ducts (Refer to AMM Task 21-20-00-410-801).

E. CLOSE-UP

(1) Subtask 573114-942-002-001 - Install/Close Items Removed/Opened for access in

the Belly Fairing Area RH side

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

Adhesion Promoter For

Polysulfide Sealant

09-028 As required

Polysulphide Fuel Tank

Sealant

09-046 As required

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801

Task 25-80-00-400-801

Task 36-22-19-400-801

Task 53-35-13-400-802

Structural Repair Manual (SRM) 51-24-00

Fig. A-FBAAA

Remove/Install the Heat Shield

Sheet 01

Sheet 02

Fig. A-FDCAA

Remove/Install the Air Conditioning

Ducts between FR39.1 and FR40 (Belly

Fairing Area)

Sheet 01

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114

REVISION No.: 00 - Mar 12/13 Page: 76

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@A330

SERVICE BULLETIN

References

Fig. A-FDBAA

Remove/Install the Air Conditioning

Ducts between FR39.1 and FR40 (Belly

Fairing Area)

Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR

CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A

GROUND SOURCE.

HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL.

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE.

NOTE: The parts removed for the access must be installed before the

SUBTASK 573114-700-002 001 Testing .

(a) Put the insulation back in position, (Refer to AMM Task 25-80-00-400-801).

(b) Install the Heat Shield of the RH Conditioning Pack refer to Fig. A-FBAAA Sheet 01

and Fig. A-FBAAA Sheet 02:

1 Heat shield Item (8) Retained at

removal

12 Screw Item (9) Retained at

removal

- Install screws Item (9) with:

Adhesion Promoter

For Polysulfide

Sealant

09-028 As required

Apply the sealant, refer to SRM 51-24-00.

Polysulphide Fuel

Tank Sealant

09-046 As required

on and around the screws.

(c) On the RH side, install the air ventilation duct (Refer to AMM Task

21-20-00-410-801 and Fig. A-FDCAA Sheet 01.

1 Install:

1 Duct Item (41) Retained at

removal

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114

REVISION No.: 00 - Mar 12/13 Page: 77

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SERVICE BULLETIN

(d) On the RH side, install the air-conditioning pack outlet duct as follows (Refer to

AMM Task 21-20-00-410-801 and Fig. A-FDBAA Sheet 01).

1 Install:

1 Duct Item (26) Retained at

removal

(e) Install the Wing Bleed-Air Duct Sensing Elements (Refer to AMM Task

36-22-19-400-801).

(f) Install the Belly Fairing Access-Panels 193DB (Refer to AMM Task

53-35-13-400-802).

(2) Subtask 573114-942-003-001 - Install/Close Item Removed/Opened for access in

the Belly Fairing Area LH side

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 53-35-13-400-802

NOTE: The parts removed for the access must be installed before the

SUBTASK 573114-700-002 001 Testing .

(a) Install the Belly Fairing Access-Panels 192PB (Refer to AMM Task

53-35-13-400-802).

(3) Subtask 573114-942-004-001 - Install/Close Items Removed/Opened for Access in

the FWD Cargo-Compartment

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801

Task 25-52-00-400-801

Task 25-80-00-400-801

Task 52-30-00-410-801

Fig. A-FDAAA

Remove/Install the Air Conditioning

Ducts between FR39.1 and FR40 (FWD

Cargo-Compartment)

Sheet 01

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE.

NOTE: The parts removed for the access must be installed before the

SUBTASK 573114-700-002 001 Testing .

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114

REVISION No.: 00 - Mar 12/13 Page: 78

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@A330

SERVICE BULLETIN

(a) On the LH and RH sides, install the air conditioning ducts between Frame 39.1 and

Frame 40 (Refer to AMM Task 21-20-00-410-801 and Fig. A-FDAAA Sheet 01).

1 Install:

2 Duct Item (11) Retained at

removal

2 Duct Item (12) Retained at

removal

2 Recirculation filterhousingItem (13) Retained at

removal

2 Recirculation fan Item (14) Retain

(b) Install the partition panels 131CX, 131DX, 132CX and 132DX (Refer to AMM Task

25-52-00-400-801).

(c) Put the insulation back in position (Refer to AMM Task 25-80-00-400-801).

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

52-30-00-410-801).

(4) Subtask 573114-942-005-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

(a) Remove all the fixtures, tools, test and support equipment used during this

procedure.

(b) Remove the access platform(s).

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

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114

REVISION No.: 00 - Mar 12/13 Page: 79

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@A330

SERVICE BULLETIN

**CONF ALL

FR47

FR40

A

C

(8)

FR40.3

FR41

FR40.2

B

Z192 Z196 − 

B

A

(12 POS) (9)

G_SB_573114_5_BAAA_01_02

Figure A-FBAAA - Sheet 01

Remove/Install the Heat Shield

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114

REVISION No.: 00 - Mar 12/13 Page: 80

5

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@A330

SERVICE BULLETIN

**CONF ALL

NOTES:

01 INSTALL SCREW ITEM (9) WITH MAT. No 09−046 (WET ASSEMBLY).

APPLY A TORQUE VALUE OF 1.65 N.m ± 0.15 (14.60 lbf.in).

02 APPLY MAT. No 09−028 and 09−046 ON AND AROUND THE SCREW.

FWD C

FR41

A

A

A A

(9)

01

02

RECEPTACLE

HEAT SHIELD

(8)

TYPICAL SECTION

G_SB_573114_5_BAAA_02_02

Figure A-FBAAA - Sheet 02

Remove/Install the Heat Shield

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114

REVISION No.: 00 - Mar 12/13 Page: 81

5

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@A330

SERVICE BULLETIN

**CONF ALL

A Z141 Z142 − 

FR47

FR40

A

B

B

G_SB_573114_5_CAAA_01_03

Figure A-FCAAA - Sheet 01

Remove/Install the fasteners

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114

REVISION No.: 00 - Mar 12/13 Page: 82

5

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@A330

SERVICE BULLETIN

**CONF ALL

FR40

LH SIDE SHOWN

RH SIDE SYMMETRICAL

STGR38

STGR39

STGR40

H25

H39

H44

H42 H41

H46 H45

H259

HOLE

SYMBOL PN DESCRIPTION REMARKS

FINAL HOLE DIAMETER

MIN MAX

6.706 mm

(0.264 in)

6.747 mm

(0.266 in)

EN6115V4−6 SCREW

ASNA2529−4 NUT

EN6115V4X6 SCREW

NUT

NOTE:

02 INSTALL THE FASTENERS WITH MAT. No 09−013 (WET ASSEMBLY)

01 DEPENDING ON INSPECTION RESULT

N

ASNA2529−4

5

7

12

7

01

02

N

HEAD ON THE VISIBLE SIDE

EXISTING HOLE DIAMETER

MIN MAX

6.227 mm

(0.245 in)

6.262 mm

(0.246 in) FIRST OVERSIZE 01

02

11.476 mm

(0.452 in)

11.515 mm

(0.453 in)

10.972 mm

(0.432 in)

11.007 mm

(0.433 in)

6.310 mm

(0.248 in)

6.350 mm

(0.250 in)

EN6115V4−10 SCREW

ASNA2529−4 NUT

EN6115V4X10 SCREW

NUT

F

ASNA2529−4

6

7

13

7

01

02

01

02

EN6115T7−18 SCREW

ASNA2531−7 NUT

EN6115T7X18 SCREW

NUT

N

ASNA2531−7

3

4

11

4

01

02

01

02

8.296 mm

(0.327 in)

8.835 mm

(0.328 in)

EN6115V5−12 SCREW

ASNA2529−5 NUT

EN6115V5X12 SCREW

NUT

N

ASNA2529−5

1

2

10

2

01

02 7.815 mm

(0.308 in)

7.849 mm

(0.309 in) 01

02

11.080 mm

(0.436 in)

11.120 mm

(0.438 in)

7.900 mm

(0.311 in)

7.940 mm

(0.312 in)

F

HEAD ON THE HIDDEN SIDE

VIEW LOOKING AFT

FASTENER

(5)

(7)

(5)

(7)

(6)

(7)

(6)

(7)

(3)

(4)

(3)

(4)

(1)

(2)

(1)

(2)

ITEM

6.706 mm

(0.264 in)

6.747 mm

(0.266 in)

6.227 mm

(0.245 in)

6.262 mm

(0.246 in)

STANDARD FASTENER

IN TRANSITION FIT

IN TRANSITION FIT

FIRST OVERSIZE

FASTENER

STANDARD FASTENER

IN TRANSITION FIT

IN TRANSITION FIT

FIRST OVERSIZE

FASTENER

STANDARD FASTENER

IN TRANSITION FIT

IN TRANSITION FIT

FIRST OVERSIZE

FASTENER

STANDARD FASTENER

IN TRANSITION FIT

IN TRANSITION FIT

6.310 mm

(0.248 in)

6.350 mm

(0.250 in)

B

AREA HOLE NUMBER

39

25, 41, 42, 44, 45, 46, 259

B

A

CENTER WING BOX LOWER PANEL REFERENCE

G_SB_573114_5_CAAA_02_05

Figure A-FCAAA - Sheet 02

Remove/Install the fasteners

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114

REVISION No.: 00 - Mar 12/13 Page: 83

5

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@A330

SERVICE BULLETIN

**CONF ALL

A Z141 Z142 − 

FR47

FR40

A

B

B

G_SB_573114_5_CBAA_01_02

Figure A-FCBAA - Sheet 01

Inspection Area

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114

REVISION No.: 00 - Mar 12/13 Page: 84

5

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@A330

SERVICE BULLETIN

**CONF ALL

FR40

LH SIDE SHOWN B RH SIDE SYMMETRICAL

VIEW LOOKING AFT

STGR38

STGR39

STGR40

H25

H39

H44

H42 H41

H46 H45

H259

NOTE:

AREA HOLE NUMBER

39

25, 41, 42, 44, 45, 46, 259

B

A

CENTER WING BOX LOWER PANEL REFERENCE

G_SB_573114_5_CBAA_02_02

Figure A-FCBAA - Sheet 02

Inspection Area

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114

REVISION No.: 00 - Mar 12/13 Page: 85

5

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@A330

SERVICE BULLETIN

**CONF ALL

A Z141 Z142 − 

FR47

FR40

A

B

B

G_SB_573114_5_CCAA_01_03

Figure A-FCCAA - Sheet 01

Remove/Install the fasteners post Service Bulletin No. A330-57-3083

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114

REVISION No.: 00 - Mar 12/13 Page: 86

5

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@A330

SERVICE BULLETIN

**CONF ALL

STGR38

STGR39

STGR40

H25

H44

H42 H41

H46 H45

H259

HOLE

SYMBOL PN DESCRIPTION

FINAL HOLE DIAMETER

MIN MAX

EN6115V5−6 SCREW

ASNA2529−5 NUT

EN6115V5X6 SCREW

NUT

N

ASNA2529−5

18

2

22

2

EXISTING HOLE DIAMETER

MIN MAX

EN6115V5−10 SCREW

ASNA2529−5 NUT

EN6115V5X10 SCREW

NUT

F

ASNA2529−5

19

2

23

2

EN6115V6−12 SCREW

ASNA2529−6 NUT

EN6115V6X12 SCREW

NUT

N

ASNA2529−6

16

17

21

17

7.815 mm

(0.308 in)

7.849 mm

(0.309 in) 8.296 mm

(0.327 in)

8.335 mm

(0.328 in)

7.900 mm

(0.311 in)

7.940 mm

(0.312 in)

9.387 mm

(0.370 in)

9.427 mm

(0.371 in) 9.886 mm

(0.389 in)

9.925 mm

(0.390 in)

9.490 mm

(0.373 in)

9.530 mm

(0.375 in)

02 INSTALL THE FASTENERS WITH MAT. No 09−013 (WET ASSEMBLY)

01 DEPENDING ON INSPECTION RESULT

FR40

LH SIDE SHOWN

RH SIDE SYMMETRICAL

VIEW LOOKING AFT

(18)

(2)

(18)

(2)

(19)

(2)

(19)

(2)

(16)

(17)

(16)

(17)

ITEM

7.815 mm

(0.308 in)

7.849 mm

(0.309 in) 8.296 mm

(0.327 in)

8.335 mm

(0.328 in)

7.900 mm

(0.311 in)

7.940 mm

(0.312 in)

REMARKS

01

02

FIRST OVERSIZE 01

02

01

02

01

02

01

02

01

02

FASTENER

STANDARD FASTENER

IN TRANSITION FIT

IN TRANSITION FIT

FIRST OVERSIZE

FASTENER

STANDARD FASTENER

IN TRANSITION FIT

IN TRANSITION FIT

FIRST OVERSIZE

FASTENER

STANDARD FASTENER

IN TRANSITION FIT

IN TRANSITION FIT

B

NOTE:

N

HEAD ON THE VISIBLE SIDE

F

HEAD ON THE HIDDEN SIDE

AREA HOLE NUMBER

A 25, 41, 42, 44, 45, 46, 259

CENTER WING BOX LOWER PANEL REFERENCE

G_SB_573114_5_CCAA_02_05

Figure A-FCCAA - Sheet 02

Remove/Install the fasteners post Service Bulletin No. A330-57-3083

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114

REVISION No.: 00 - Mar 12/13 Page: 87

5

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@A330

SERVICE BULLETIN

**CONF ALL

RH SIDE SHOWN

LH SIDE SYMMETRICAL

Z130

FR39.1

FR40

(11) (12)

(14)

(13)

B

B

B

A

A

G_SB_573114_5_DAAA_01_00

Figure A-FDAAA - Sheet 01

Remove/Install the Air Conditioning Ducts between FR39.1 and FR40 (FWD Cargo-Compartment)

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114

REVISION No.: 00 - Mar 12/13 Page: 88

5

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@A330

SERVICE BULLETIN

**CONF ALL

A

B

FR39.2

FR40.2

A

B

(26)

Z192

G_SB_573114_5_DBAA_01_00

Figure A-FDBAA - Sheet 01

Remove/Install the Air Conditioning Ducts between FR39.1 and FR40 (Belly Fairing Area)

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114

REVISION No.: 00 - Mar 12/13 Page: 89

5

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@A330

SERVICE BULLETIN

**CONF ALL

FR39.2

FR40.2

B

(41)

A

B

A Z192

G_SB_573114_5_DCAA_01_00

Figure A-FDCAA - Sheet 01

Remove/Install the Air Conditioning Ducts between FR39.1 and FR40 (Belly Fairing Area)

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114

REVISION No.: 00 - Mar 12/13 Page: 90

5

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@A330

SERVICE BULLETIN

**CONF ALL

QUESTION

ACTION

FINDING

AT THE THRESHOLD GIVEN IN THE TABLES 1 AND 2

OF THE PLANNING INFORMATION PARAGRAPH E.(2).

(REFER TO SUBTASK 573114−832−001 AND 573114−832−002) AND

RH SIDE (REFER TO SUBTASK 573114−832−006 AND 573114−832−007)

CRACKS YES NO

INSTALL NEW SAME FASTENER OF THE

AREA B

(REFER TO SUBTASK 573114−832−005) AND

DO A ROTOTEST INSPECTION OF THE FASTENER

HOLE OF THE AREA B OF THE FRAME 40, LH AND RH SIDES

FOUND

(REFER TO SUBTASK 573114−832−005)

OF THE FASTENER HOLE OF THE

AREA B OF THE FRAME 40,

SEE FIG. A−FFAAA

SHEET 04

SEE FIG. A−FFAAA

SHEET 04

AREA B IN TRANSITION FIT, LH AND

(REFER TO SUBTASK 573114−833−002) AND

DO A SPECIAL DETAILED INSPECTION OF THE FASTENER HOLES

OF THE AREAS A AND B OF THE FRAME 40, LH SIDE

REPEAT THE ROTOTEST INSPECTION

AREA A

ALI 57−11−04 YES NO ACCOMPLISHED

SEE FIG. A−FFAAA

SHEET 03

SEE FIG. A−FFAAA

SHEET 02

LH AND RH SIDES

(REFER TO SUBTASK 573114−833−014)

RH SIDES, BEFORE NEXT FLIGHT

AND

AT THE INTERVAL GIVEN IN THE

(REFER TO SUBTASK 573114−832−010)

(REFER TO SUBTASK 573114−832−010)

AT THE THRESHOLD GIVEN IN THE TABLE 5 OF

THE PLANNING INFORMATION PARAGRAPH E.(2).

HOLE 39 HOLES 25, 41, 42,

44, 45, 46 AND 259

TABLE 5 OF THE PLANNING

INFORMATION PARAGRAPH E.(2).

G_SB_573114_5_FAAA_01_03

Figure A-FFAAA - Sheet 01

Flow Chart

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114

REVISION No.: 00 - Mar 12/13 Page: 91

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@A330

SERVICE BULLETIN

**CONF ALL

NOTE:

01 THRESHOLD TO BE COUNTED FROM MSB 57−3083 EMBODIMENT

QUESTION

ACTION

FINDING

CRACKS

OR

(REFER TO SUBTASK 573114−832−003) AND

SB No A330−57−3083 OF THE FASTENER HOLES OF

THE AREA A OF THE FRAME 40, LH AND RH SIDES

FOUND

A330−57−3083 NO YES ACCOMPLISHED

SEE FIG. A−FFAAA

SHEET 01

SB No

CRACKS YES NO

(REFER TO SUBTASK 573114−832−004) AND

FOUND

SEE FIG. A−FFAAA

SHEET 04

SEE FIG. A−FFAAA SHEET 04

OR

(REFER TO SUBTASK 573114−832−003) AND

SB No A330−57−3083 OF THE FASTENER HOLES OF

THE AREA A OF THE FRAME 40, LH AND RH SIDES

APPLY SB No A330−57−3083

YES NO

SEE FIG. A−FFAAA

SHEET 04

(SB No A330−57−3083

ACCOMPLISHED)

SEE FIG. A−FFAAA SHEET 04

(SB No A330−57−3083

NOT ACCOMPLISHED)

INSTALL NEW SAME FASTENERS PRE SB No A330−57−3083

OF THE AREA A IN TRANSITION FIT, LH AND RH SIDES,

THE AREA A OF THE FRAME 40, LH AND RH SIDES

DO A ROTOTEST INSPECTION PRE SB No A330−57−3083 OF THE FASTENER HOLES OF

DO A ROTOTEST INSPECTION POST

REPEAT THE ROTOTEST INSPECTION PRE (REFER TO SUBTASK 573114−832−004) AND

SB No A330−57−3083 OF THE FASTENER HOLES OF

THE AREA A OF THE FRAME 40, LH AND RH SIDES

INSTALL NEW SAME FASTENERS POST SB No A330−57−3083

(REFER TO SUBTASK 573114−833−007) AND

REPEAT THE ROTOTEST INSPECTION POST

01

BEFORE NEXT FLIGHT

(REFER TO SUBTASK 573114−832−008)

AT THE THRESHOLD GIVEN IN THE TABLE 3 OF

THE PLANNING INFORMATION PARAGRAPH E.(2).

(REFER TO SUBTASK 573114−832−009)

AT THE THRESHOLD GIVEN IN THE TABLE 4 OF

THE PLANNING INFORMATION PARAGRAPH E.(2).

(REFER TO SUBTASK 573114−832−008)

AT THE INTERVAL GIVEN IN THE TABLE 3 OF

THE PLANNING INFORMATION PARAGRAPH E.(2).

(REFER TO SUBTASK 573114−833−013)

(REFER TO SUBTASK 573114−832−009)

AT THE INTERVAL GIVEN IN THE TABLE 4 OF

THE PLANNING INFORMATION PARAGRAPH E.(2).

BEFORE NEXT FLIGHT

(REFER TO SUBTASK 573114−833−001) AND

(REFER TO SUBTASK 573114−833−012)

OF THE AREA A IN TRANSITION FIT, LH AND RH SIDES,

BEFORE NEXT FLIGHT

G_SB_573114_5_FAAA_02_04

Figure A-FFAAA - Sheet 02

Flow Chart

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114

REVISION No.: 00 - Mar 12/13 Page: 92

5

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@A330

SERVICE BULLETIN

**CONF ALL

QUESTION

ACTION

FINDING

NOTE:

THRESHOLD TO BE COUNTED FROM MSB 57−3083 EMBODIMENT

INITIAL INTERVAL TO BE COUNTED FROM ALI 57−11−04 EMBODIMENT

01

02

CRACKS

OR

(REFER TO SUBTASK 573114−832−003) AND

SB No A330−57−3083 OF THE FASTENER HOLES OF

THE AREA A OF THE FRAME 40, LH AND RH SIDES

FOUND

A330−57−3083 NO YES ACCOMPLISHED

SEE FIG. A−FFAAA

SHEET 01

SB No

CRACKS YES NO

(REFER TO SUBTASK 573114−832−004) AND

FOUND

SEE FIG. A−FFAAA

SHEET 04

SEE FIG. A−FFAAA SHEET 04

OR

(REFER TO SUBTASK 573114−832−003) AND

SB No A330−57−3083 OF THE FASTENER HOLES OF

THE AREA A OF THE FRAME 40, LH AND RH SIDES

APPLY SB No A330−57−3083

YES NO

SEE FIG. A−FFAAA

SHEET 04

(SB No A330−57−3083

ACCOMPLISHED)

SEE FIG. A−FFAAA SHEET 04

(SB No A330−57−3083

NOT ACCOMPLISHED)

INSTALL NEW SAME FASTENERS PRE SB No A330−57−3083

(REFER TO SUBTASK 573114−833−001) AND

THE AREA A OF THE FRAME 40, LH AND RH SIDES

DO A ROTOTEST INSPECTION PRE SB No A330−57−3083 OF THE FASTENER HOLES OF

DO A ROTOTEST INSPECTION POST

REPEAT THE ROTOTEST INSPECTION PRE (REFER TO SUBTASK 573114−832−004) AND

SB No A330−57−3083 OF THE FASTENER HOLES OF

THE AREA A OF THE FRAME 40, LH AND RH SIDES

INSTALL NEW SAME FASTENERS POST SB No A330−57−3083

(REFER TO SUBTASK 573114−833−007) AND

REPEAT THE ROTOTEST INSPECTION POST

02 01 BEFORE NEXT FLIGHT

(REFER TO SUBTASK 573114−832−008)

AT THE INTERVAL GIVEN IN THE TABLE 3 OF

THE PLANNING INFORMATION PARAGRAPH E.(2).

(REFER TO SUBTASK 573114−833−012)

(REFER TO SUBTASK 573114−832−008)

AT THE INTERVAL GIVEN IN THE TABLE 3 OF

THE PLANNING INFORMATION PARAGRAPH E.(2).

(REFER TO SUBTASK 573114−832−009)

AT THE THRESHOLD GIVEN IN THE TABLE 4 OF

THE PLANNING INFORMATION PARAGRAPH E.(2).

(REFER TO SUBTASK 573114−833−013)

(REFER TO SUBTASK 573114−832−009)

AT THE INTERVAL GIVEN IN THE TABLE 4 OF

THE PLANNING INFORMATION PARAGRAPH E.(2).

OF THE AREA A IN TRANSITION FIT, LH AND RH SIDES,

BEFORE NEXT FLIGHT

OF THE AREA A IN TRANSITION FIT, LH AND RH SIDES,

BEFORE NEXT FLIGHT

G_SB_573114_5_FAAA_03_04

Figure A-FFAAA - Sheet 03

Flow Chart

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114

REVISION No.: 00 - Mar 12/13 Page: 93

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@A330

SERVICE BULLETIN

**CONF ALL

QUESTION

ACTION

FINDING

CRACKS YES NO FOUND

NO YES

SEE FIG. A−FFAAA

SHEET 01, SHEET 02 AND SHEET 03

INSTALL NEW FASTENER PRE OR POST

THE CURRENT HOLE DIAMETER AND DO A ROTOTEST INSPECTION,

OVERSIZE THE HOLES OF THE AREA A PRE OR POST

SB No A330−57−3083 TO FIRST OVERSIZE IN COMPARISON WITH

(REFER TO SUBTASK 573114−833−003 AND 573114−833−015) OR

SEE FIG. A−FFAAA SHEET 02 AND 03

(SB No A330−57−3083

NOT ACCOMPLISHED)

SEE FIG. A−FFAAA SHEET 02 AND 03

(SB No A330−57−3083

ACCOMPLISHED)

SEE FIG. A−FFAAA SHEET 01

A330−57−3083

ACCOMPLISHED

SB No

SB No A330−57−3083 OF THE AREA A

(REFER TO SUBTASK 573114−833−011 AND 573114−833−016)

(REFER TO SUBTASK 573114−832−003) AND

SB No A330−57−3083 OF THE FASTENER HOLES OF

THE AREA A OF THE FRAME 40, LH AND RH SIDES,

REPEAT THE ROTOTEST INSPECTION PRE

(REFER TO SUBTASK 573114−832−004) AND

SB No A330−57−3083 OF THE FASTENER HOLES OF

REPEAT THE ROTOTEST INSPECTION POST

IN TRANSITION FIT, LH AND RH SIDES, BEFORE NEXT FLIGHT

CRACKS YES NO FOUND

INSTALL NEW FASTENER OF THE

HOLE DIAMETER AND DO A ROTOTEST INSPECTION,

OVERSIZE THE HOLE OF THE AREA B TO

FIRST OVERSIZE IN COMPARISON WITH THE CURRENT

(REFER TO SUBTASK 573114−833−010) AND

CONTACT AIRBUS

AREA B IN TRANSITION FIT, LH AND RH SIDES, 

(REFER TO SUBTASK 573114−833−006) AND

(REFER TO SUBTASK 573114−832−005) AND

OF THE FASTENER HOLE OF THE AREA B

OF THE FRAME 40, LH AND RH SIDES

REPEAT THE ROTOTEST INSPECTION

THE AREA A OF THE FRAME 40, LH AND RH SIDES,

LH AND RH SIDES, BEFORE NEXT FLIGHT LH AND RH SIDES, BEFORE NEXT FLIGHT

BEFORE NEXT FLIGHT

CONTACT AIRBUS

BEFORE NEXT FLIGHT

(REFER TO SUBTASK 573114−833−005 AND 573114−833−018)

OR

(REFER TO SUBTASK 573114−833−009 AND 573114−833−019)

(REFER TO SUBTASK 573114−833−020)

BEFORE NEXT FLIGHT

(REFER TO SUBTASK 573114−832−010)

AT THE INTERVAL GIVEN IN THE TABLE 5 OF

THE PLANNING INFORMATION PARAGRAPH E.(2).

(REFER TO SUBTASK 573114−832−008)

AT THE INTERVAL GIVEN IN THE TABLE 3 OF

THE PLANNING INFORMATION PARAGRAPH E.(2).

(REFER TO SUBTASK 573114−832−009)

AT THE INTERVAL GIVEN IN THE TABLE 4 OF

THE PLANNING INFORMATION PARAGRAPH E.(2).

(REFER TO SUBTASK 573114−833−017)

AREA A AREA B

HOLES 25, 41, 42, 44, 45, 46 AND 259 HOLE 39

G_SB_573114_5_FAAA_04_05

Figure A-FFAAA - Sheet 04

Flow Chart

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114

REVISION No.: 00 - Mar 12/13 Page: 94

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@A330

SERVICE BULLETIN

Appendix 01 : Inspection Report

**CONF ALL

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

forwarded to AIRBUS Department SEES1, on the attached inspection report sheet.

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114

REVISION No.: 00 - Mar 12/13 Page: 1

5

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@A330

SERVICE BULLETIN

Appendix 01 : Inspection Report

**CONF ALL

INSPECTION REPORT

SERVICE BULLETIN No. :

A/C MSN :

FLIGHT CYCLES :

FLIGHT HOURS :

A330−57−3114

DATE OF INSPECTION :

RETURN TO :

AIRBUS

CUSTOMER SERVICES ENGINEERING − SEES1

FUSELAGE (WB/LR) − VERTICAL TAIL PLANE − 

INSPECTION METHOD :

LH SIDE

ROTOTEST

CRACKS

YES

INSPECTION

CENTER WING BOX (WB/LR)

1 ROND POINT MAURICE BELLONTE

31707 BLAGNAC CEDEX

FRANCE

FAX +33 (0)5 61 93 36 14

CRACKS AFTER

OVERSIZE

H25 NO

CRACKS CRACKS AFTER

OVERSIZE

YES NO YES NO YES NO

RH SIDE

H39 YES NO YES NO YES NO YES NO

H41 YES NO YES NO YES NO YES NO

H42 YES NO YES NO YES NO YES NO

H44 YES NO YES NO YES NO YES NO

H45 YES NO YES NO YES NO YES NO

H46 YES NO YES NO YES NO YES NO

H259 YES NO YES NO YES NO YES NO

E−mail: Structure.sbinspectionresult@airbus.com

G_SB_573114_5_RAAA_01_01

Figure A-FRAAA - Sheet 01

Appendix 01 : Inspection Report

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114

REVISION No.: 00 - Mar 12/13 Page: 2

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A330

SERVICE BULLETIN

Appendix 01 : Inspection Report

**CONF ALL

INSPECTION REPORT

SERVICE BULLETIN No. :

A/C MSN :

FLIGHT CYCLES :

FLIGHT HOURS :

A330−57−3114

DATE OF INSPECTION :

RETURN TO :

AIRBUS

CUSTOMER SERVICES ENGINEERING − SEES1

FUSELAGE (WB/LR) − VERTICAL TAIL PLANE − 

INSPECTION METHOD :

LH SIDE

ROTOTEST

mm

INSPECTION

CENTER WING BOX (WB/LR)

1 ROND POINT MAURICE BELLONTE

31707 BLAGNAC CEDEX

FRANCE

FAX +33 (0)5 61 93 36 14

FINAL

DIAMETER

H25 in

RH SIDE

E−mail: Structure.sbinspectionresult@airbus.com

INITIAL

DIAMETER

FINAL

DIAMETER

INITIAL

DIAMETER

mm in mm in mm in

H39 mm in mm in mm in mm in

H41 mm in mm in mm in mm in

H42 mm in mm in mm in mm in

H44 mm in mm in mm in mm in

H45 mm in mm in mm in mm in

H46 mm in mm in mm in mm in

H259 mm in mm in mm in mm in

G_SB_573114_5_RAAA_02_01

Figure A-FRAAA - Sheet 02

Appendix 01 : Inspection Report

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114

REVISION No.: 00 - Mar 12/13 Page: 3

5

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@A330

SERVICE BULLETIN

Appendix 01 : Inspection Report

**CONF ALL

FR40

VIEW LOOKING AFT

STGR38

STGR39

STGR40

H25

H39

H44

H42 H41

H46 H45

H259

LH SIDE SHOWN

RH SIDE SYMMETRICAL

CENTER WING BOX LOWER PANEL REFERENCE

G_SB_573114_5_RAAA_03_00

Figure A-FRAAA - Sheet 03

Appendix 01 : Inspection Report

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114

REVISION No.: 00 - Mar 12/13 Page: 4

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A330

SERVICE BULLETIN

Appendix 01 : Inspection Report

**CONF ALL

FR40 FRONT

FITTING

(8.5 mm)

(0.335 in)

FR40 REAR

FITTING

(9.2 mm)

(0.362 in)

HOLE 25

FWD

NOTE:

THESE THICKNESSES ARE THEORETICAL

HOLE 39

HOLE 41, 42, 44, 46 HOLE 45, 259

FR40 POST

Y1959

(6 mm)

(0.236 in)

FITTING

Y1959

(12 mm)

(0.472 in) FR40 SPAR

WEB

(4 mm)

(0.157 in)

FR40 REAR

FITTING

(5 mm)

(0.197 in)

FWD

FWD

FWD

FR40 SPAR

WEB

(4 mm)

(0.157 in)

FR40 REAR

FITTING

(5 mm)

(0.197 in)

FR40

ORBITAL TEE

(6 mm)

(0.236 in) FR40 SPAR

WEB

(4 mm)

(0.157 in)

FR40 REAR

FITTING

(5 mm)

(0.197 in)

AFT LOWER

G_SB_573114_5_RAAA_04_01

Figure A-FRAAA - Sheet 04

Appendix 01 : Inspection Report

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114

REVISION No.: 00 - Mar 12/13 Page: 5

5

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@A330

SERVICE BULLETIN

REPORTING SHEET

TITLE: WINGS - CENTER WING BOX - INSPECTION OF FASTENER HOLES AT

FRAME 40 VERTICAL WEB BELOW INTRADOS

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: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114

REVISION No.: 00 - Mar 12/13 Page: 1

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SERVICE BULLETIN

QUALITY PERCEPTION FORM

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

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

improve the quality of our Service Bulletins.

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

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

- Quality rating of this SB 4321

- Quality rating of the Accomplishment Instructions 4321

- Quality rating of the Illustrations 4321

- Is this SB easy to understand ? Y/N

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

short description of the issue.

Planning Material Instructions

X Effectivity X Kit content X Preparation

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

X Manpower X Industry support X Test

X References X Re-identification X Close-Up

X Publication X Tooling X Illustrations

Comments:

Operator: Date:

Name/Title:

Please return this form to:

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX FRANCE

Attn : SEM4 Service Bulletins Management

FAX : (33) 5 61 93 42 51

Or via your Resident Customer Support Office.

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114

REVISION No.: 00 - Mar 12/13 Page: 1

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