@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: 53

TITLE: FUSELAGE - CENTER FUSELAGE - INSPECTION OF FUSELAGE

INTERNAL STRUCTURE, FASTENER HOLE AREA ABOVE STRINGER

28 AT FRAME 39.1 WEB JUNCTION ON HOIST FITTING, LH/RH

**CONF ALL

MODIFICATIONS

None

REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

Further to a query from an operator on Feb 26/2010, AIRBUS was asked to clarify if Maintenance

Planning Document (MPD) 533105-01-2 / Airworthiness Limitation Items (ALI) 533105-01-02 is

applicable to A330 aircraft MSN 0012 and 0017.

Customization and Delivery Information Services (CDIS) - Aircraft Inspection Report (AIR) indicates that

Mod. No. 40391S10374 (MODIFY THE REINFORCEMENT TO INSTALL THE HANDLING FITTING AT

FR39.1) is fully embodied on aircraft MSN 0012 and 0017.

However, Mod. No. 40391S10374 was embodied on aircraft MSN 0029 and subsequent.

After review, AIRBUS confirmed that aircraft MSN 0012 and 0017 do not have Mod. No. 40391S10374

embodied and therefore these aircraft are subjected to above ALI task.

The AIR do not reflect the true aircraft configuration. MSN 0012 and 0017 are pre-Mod. No.

40391S10374.

Aircraft MSN 0012 and 0017 are the only two A330 aircraft manufactured prior to effectivity of Mod. No.

40391S10374.

For these two CPA aircraft having already exceeded the ALI threshold, an additional compliance time

was calculated.

This Service Bulletin mandates the inspection steps of ALI 533105 as per NTM 53-31-05 on A330

aircraft MSN 0012 and 0017, that is a special detailed inspection of fuselage internal structure, fastener

hole area above stringer 28 at Frame 39.1 web junction on hoist fitting (LH and RH side).

DATE: May 20/10 SERVICE BULLETIN No.: A330-53-3185

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SERVICE BULLETIN

SUMMARY

Accomplishment of this Service Bulletin will restore the situation for this pre Mod. No. 40391S10374

area with regards to the airworthiness requirements.

The ALI task will be cancelled and this Inspection Service Bulletin (ISB) will be used as the source

document in the MPD (to be amended at next revision).

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 NO VENDOR SB INVOLVED NO

NOTE (1): Service Bulletin must be accomplished.

MATERIAL PRICE INFORMATION

**CONF 001

No Material

**CONF 002

No Material

EFFECTIVITY

**CONF ALL

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

CPA

CONCURRENT REQUIREMENTS

None

REFERENCES / REPERCUSSIONS

TFU None

OEB None

AOT None

SIL None

LINE MAINTENANCE AFFECTED No

LIFE LIMIT None

OTHER None

NATURE OF THE WORK

AIRCRAFT YES

EQUIPMENT NO

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SUMMARY

HARD NO

SOFT NO

OBRM NO

MANPOWER

**CONF 001

Task 533185-832-801-001: Inspection

TOTAL MANHOURS 14.50

ELAPSED TIME (HOURS) 8.50

**CONF 002

Task 533185-832-801-001: Inspection

TOTAL MANHOURS 14.50

ELAPSED TIME (HOURS) 8.50

APPENDICES

**CONF ALL

Appendix 01

Appendix 02

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SERVICE BULLETIN

SUMMARY

**CONF ALL

FITTING INSPECTION AREA

AREA TO BE INSPECTED

NOTE:

A

A

A

FR39.1

A A

LH SIDE SHOWN

RH SIDE SYMMETRICAL

A

G_SB_533185_5_SAAA_01_02

FITTING

MEMBER−ARCH

STGR28

STGR29

STGR30

Figure A-FSAAA - Sheet 01

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SERVICE BULLETIN

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX

FRANCE

Tel : (33) 5 61 93 33 33

Telex : AIRBU 530526F

Fax : (33) 5 61 93 42 51

MANDATORY MANDATORY MANDATORY

ATA SYSTEM: 53

TITLE: FUSELAGE - CENTER FUSELAGE - INSPECTION OF FUSELAGE

INTERNAL STRUCTURE, FASTENER HOLE AREA ABOVE STRINGER

28 AT FRAME 39.1 WEB JUNCTION ON HOIST FITTING, LH/RH

MODIFICATION No.: None

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

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

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

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

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

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

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

AIRBUS prior written consent.

1. PLANNING INFORMATION

**CONF ALL

A. EFFECTIVITY

(1) Models

330-342

(2) Effectivity by MSN

0012 0017

(3) Effectivity by Operator

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

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

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

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

OPERATOR MSN

CPA 0012 0017

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(4) Configuration by MSN

MSN CONFIGURATION

0012 001

0017 002

(5) Configuration definition

**CONF 001

Config. 001 is valid for aircraft MSN 0012.

**CONF 002

Config. 002 is valid for aircraft MSN 0017.

(6) Material Effectivity

MATERIAL QTY PER A/C SEE NOTES

Consumable CMLA01 As required

B. CONCURRENT REQUIREMENTS

None

C. REASON

(1) History

Further to a query from an operator on Feb 26/2010, AIRBUS was asked to clarify if

Maintenance Planning Document (MPD) 533105-01-2 / Airworthiness Limitation Items

(ALI) 533105-01-02 is applicable to A330 aircraft MSN 0012 and 0017.

Customization and Delivery Information Services (CDIS) - Aircraft Inspection Report

(AIR) indicates that Mod. No. 40391S10374 (MODIFY THE REINFORCEMENT TO

INSTALL THE HANDLING FITTING AT FR39.1) is fully embodied on aircraft MSN 0012

and 0017.

However, Mod. No. 40391S10374 was embodied on aircraft MSN 0029 and subsequent.

After review, AIRBUS confirmed that aircraft MSN 0012 and 0017 do not have Mod. No.

40391S10374 embodied and therefore these aircraft are subjected to above ALI task.

The AIR do not reflect the true aircraft configuration. MSN 0012 and 0017 are pre-Mod.

No. 40391S10374.

Aircraft MSN 0012 and 0017 are the only two A330 aircraft manufactured prior to

effectivity of Mod. No. 40391S10374.

For these two CPA aircraft having already exceeded the ALI threshold, an additional

compliance time was calculated.

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SERVICE BULLETIN

(2) Objective/Action

This Service Bulletin mandates the inspection steps of ALI 533105 as per NTM 53-31-05

on A330 aircraft MSN 0012 and 0017, that is a special detailed inspection of fuselage

internal structure, fastener hole area above stringer 28 at Frame 39.1 web junction on

hoist fitting (LH and RH side).

(3) Advantages

Accomplishment of this Service Bulletin will restore the situation for this pre Mod. No.

40391S10374 area with regards to the airworthiness requirements.

(4) Operational/Maintenance Consequences

The ALI task will be cancelled and this Inspection Service Bulletin (ISB) will be used as

the source document in the MPD (to be amended at next revision).

D. DESCRIPTION

To accomplish this Service Bulletin it is necessary to :

**CONF 001

Task 533185-832-801-001: Inspection

(1) Do a Special Detailed Inspection of LH Frame 39.1

(2) Do a Special Detailed Inspection of RH Frame 39.1

**CONF 002

Task 533185-832-801-001: Inspection

(1) Do a Special Detailed Inspection of LH Frame 39.1

(2) Do a Special Detailed Inspection of RH Frame 39.1

**CONF ALL

E. COMPLIANCE

(1) Classification

MANDATORY: Service Bulletin must be accomplished.

(2) Accomplishment Timescale

**CONF 001

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

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

Agency (EASA). It is anticipated that the AD will confirm the thresholds and intervals

given below but reference should be made to the AD for confirmation of the mandated

accomplishment timescale.

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COMPLIANCE TIME (whichever occurs

first)

CONDITION ACTION

THRESHOLD GRACE PERIOD

REPETITIVE

INTERVAL NOT

TO EXCEED

(whichever occurs

first)

CONF 001 Inspect in

accordance with

SUBTASK

533185-832-001

001 Do a Special

Detailed Inspection

of LH Frame 39.1

and SUBTASK

533185-832-002

001 Do a Special

Detailed Inspection

of RH Frame 39.1 .

16,200 Flight

Cycles (FC) /

38,900 Flight

Hours (FH) from

the first flight

- 7,400 FC / 22,300

FH

Crack(s) found Contact AIRBUS

and follow their

corrective action.

Before next flight Not applicable

No crack(s) found Do the inspection

again in

accordance with

SUBTASK

533185-832-001

001 Do a Special

Detailed Inspection

of LH Frame 39.1

and SUBTASK

533185-832-002

001 Do a Special

Detailed Inspection

of RH Frame 39.1 .

Interval not exceeding 7,400 FC /

22,300 FH

Not applicable

**CONF 002

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

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

Agency (EASA). It is anticipated that the AD will confirm the thresholds and intervals

given below but reference should be made to the AD for confirmation of the mandated

accomplishment timescale.

COMPLIANCE TIME (whichever occurs

first)

CONDITION ACTION

THRESHOLD GRACE PERIOD

REPETITIVE

INTERVAL NOT

TO EXCEED

(whichever occurs

first)

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SERVICE BULLETIN

CONF 002 Inspect in

accordance with

SUBTASK

533185-832-001

001 Do a Special

Detailed Inspection

of LH Frame 39.1

and SUBTASK

533185-832-002

001 Do a Special

Detailed Inspection

of RH Frame 39.1 .

16,200 FC / 38,000

FH from the first

flight

- 7,400 FC / 22,300

FH

Crack(s) found Contact AIRBUS

and follow their

corrective action.

Before next flight Not applicable

No crack(s) found Do the inspection

again in

accordance with

SUBTASK

533185-832-001

001 Do a Special

Detailed Inspection

of LH Frame 39.1

and SUBTASK

533185-832-002

001 Do a Special

Detailed Inspection

of RH Frame 39.1 .

Interval not exceeding 7,400 FC /

22,300 FH

Not applicable

**CONF ALL

F. APPROVAL

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

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

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

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

before incorporation of the Service Bulletin.

G. MANPOWER

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

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

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

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

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

included.

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**CONF 001

Task 533185-832-801-001: Inspection

Get Access 5.00

On Aircraft

Do a Special Detailed Inspection of LH Frame 39.1 1.00

Do a Special Detailed Inspection of RH Frame 39.1 1.00

Tests 0.50

Close-Up 7.00

TOTAL MANHOURS 14.50

ELAPSED TIME (HOURS) 8.50

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

**CONF 002

Task 533185-832-801-001: Inspection

Get Access 5.00

On Aircraft

Do a Special Detailed Inspection of LH Frame 39.1 1.00

Do a Special Detailed Inspection of RH Frame 39.1 1.00

Tests 0.50

Close-Up 7.00

TOTAL MANHOURS 14.50

ELAPSED TIME (HOURS) 8.50

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

**CONF ALL

H. WEIGHT AND BALANCE

Not Changed

I. ELECTRICAL LOAD DATA

Not Changed

J. REFERENCES

**CONF 001

Aircraft Maintenance Manual (AMM) 06-41-53 12-34-24 25-52-00

52-30-00

Consumable Material List (CML)

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

Maintenance Planning Document (MPD) 533105-01-2

Non Destructive Test Manual (NTM) 53-31-05

Structural Repair Manual (SRM) 51-23-12

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**CONF 002

Aircraft Maintenance Manual (AMM) 06-41-53 12-34-24 25-52-00

52-30-00

Consumable Material List (CML)

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

Maintenance Planning Document (MPD) 533105-01-2

Non Destructive Test Manual (NTM) 53-31-05

Structural Repair Manual (SRM) 51-23-12

**CONF ALL

K. PUBLICATION AFFECTED

Impact on scheduled maintenance : Refer to A330 Maintenance Planning Document

533105-01-2.

L. INTERCHANGEABILITY/MIXABILITY

Not Applicable

M. SPARES

None

DATE: May 20/10 SERVICE BULLETIN No.: A330-53-3185

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This Page Intentionally Left Blank

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2. MATERIAL INFORMATION

**CONF ALL

A. MATERIAL - PRICE AND AVAILABILITY

(1) Procurement Addresses

None

(2) Price and Availability

None

B. INDUSTRY SUPPORT INFORMATION

AIRBUS will not provide industry support for accomplishment of this Service Bulletin.

C. LIST OF COMPONENTS

No Kit

D. LIST OF MATERIALS - OPERATOR SUPPLIED

(1) Consumable Materials

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO CML

MAT. No.

QTY PER A/C SEE

NOTES

Trichloroethane (methyl Chloroform) 11-004 As required

Corrosion Preventive Temporary

Protective Compound

15-005A As required

Lint-Free Cotton Cloth 19-003 As required

(2) Components

None

(3) Equipment

None

E. PARTS TO BE RE-IDENTIFIED BY OPERATOR

None

F. TOOLING

None

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3. ACCOMPLISHMENT INSTRUCTIONS

Task 533185-832-801-001 - Inspection

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

INCLUDED IN THE REFERENCED PROCEDURES.

CAUTION: ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP

ELECTRICAL WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY

AND MECHANICALLY SERVICEABLE). WHEN YOU DO MAINTENANCE

WORK, REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING,

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

THIS :

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

NECESSARY ON WIRING AND COMPONENTS.

- REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND

OTHER CONTAMINATION.

THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION

AND DAMAGE TO THE ELECTRICAL WIRING INSTALLATION.

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

Task Associated Data

**CONF 001

Zone

130

Manpower

TOTAL MANHOURS 14.50

ELAPSED TIME (HOURS) 8.50

**CONF 002

Zone

130

Manpower

TOTAL MANHOURS 14.50

ELAPSED TIME (HOURS) 8.50

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**CONF ALL

A. GENERAL

**CONF 001

(1) Subtask 533185-839-001-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

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

Service Bulletin.

(2) Subtask 533185-910-001-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Trichloroethane (methyl

Chloroform)

11-004 As required

Corrosion Preventive

Temporary Protective

Compound

15-005A As required

Lint-Free Cotton Cloth 19-003 As required

References

Consumable Material List (CML)

Structural Repair Manual (SRM) 51-23-12

(a) If necessary, clean the surfaces to be inspected with :

Trichloroethane

(methyl Chloroform)

11-004 As required

and

Lint-Free Cotton

Cloth

19-003 As required

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(b) Renew the protective finish with :

Corrosion

Preventive

Temporary

Protective

Compound

15-005A As required

(Refer to SRM 51-23-12).

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

Material List (CML).

**CONF 002

(1) Subtask 533185-839-001-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

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

Service Bulletin.

(2) Subtask 533185-910-001-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Trichloroethane (methyl

Chloroform)

11-004 As required

Corrosion Preventive

Temporary Protective

Compound

15-005A As required

Lint-Free Cotton Cloth 19-003 As required

References

Consumable Material List (CML)

Structural Repair Manual (SRM) 51-23-12

(a) If necessary, clean the surfaces to be inspected with :

Trichloroethane

(methyl Chloroform)

11-004 As required

and

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Lint-Free Cotton

Cloth

19-003 As required

(b) Renew the protective finish with :

Corrosion

Preventive

Temporary

Protective

Compound

15-005A As required

(Refer to SRM 51-23-12).

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

Material List (CML).

**CONF ALL

B. PREPARATION

**CONF 001

(1) Subtask 533185-941-001-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

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

Task 12-34-24-860-802

Task 25-52-00-000-801

Task 52-30-00-010-801

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

12-34-24-860-802).

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

52-30-00-010-801).

(c) Put access platform(s) in position.

(d) If necessary, remove the ceiling panels 131VC and 132VC(Refer to AMM 06-41-53,

Page Block 001 and AMM Task 25-52-00-000-801).

(e) Remove the partition panels 131DX and 132DX(Refer to AMM 06-41-53, Page

Block 001 and AMM Task 25-52-00-000-801).

(f) Remove the sidewall panels 131AX and 132AX(Refer to AMM 06-41-53, Page

Block 001 and AMM Task 25-52-00-000-801).

(g) Lift the necessary insulation blankets.

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**CONF 002

(1) Subtask 533185-941-001-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

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

Task 12-34-24-860-802

Task 25-52-00-000-801

Task 52-30-00-010-801

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

12-34-24-860-802).

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

52-30-00-010-801).

(c) Put access platform(s) in position.

(d) If necessary, remove the ceiling panels 131VC and 132VC(Refer to AMM 06-41-53,

Page Block 001 and AMM Task 25-52-00-000-801).

(e) Remove the partition panels 131DX and 132DX(Refer to AMM 06-41-53, Page

Block 001 and AMM Task 25-52-00-000-801).

(f) Remove the sidewall panels 131AX and 132AX(Refer to AMM 06-41-53, Page

Block 001 and AMM Task 25-52-00-000-801).

(g) Lift the necessary insulation blankets.

**CONF ALL

C. PROCEDURE

**CONF 001

(1) Subtask 533185-832-001-001 - Do a Special Detailed Inspection of LH Frame 39.1

Work Zones and Access Panels

Zone Access/Work location

130 Work location Frame 39.1

Stringer 28

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills NON DESTRUCTIVE

TESTING

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References

Non Destructive Test Manual (NTM) 53-31-05

Fig. A-FBAAA

Area to be Inspected

Sheet 01

Fig. A-FBBAA

Flow Chart

Sheet 01

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

(b) Do a special detailed inspection of the LH Frame 39.1 at hole area just above

stringer 28 as per NTM 53-31-05.

Refer to Fig. A-FBBAA Sheet 01.

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

(2) Subtask 533185-832-002-001 - Do a Special Detailed Inspection of RH Frame 39.1

Work Zones and Access Panels

Zone Access/Work location

130 Work location Frame 39.1

Stringer 28

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills NON DESTRUCTIVE

TESTING

References

Non Destructive Test Manual (NTM) 53-31-05

Fig. A-FBAAA

Area to be Inspected

Sheet 01

Fig. A-FBBAA

Flow Chart

Sheet 01

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

(b) Do a special detailed inspection of the RH Frame 39.1 at hole area just above

stringer 28 as per NTM 53-31-05.

Refer to Fig. A-FBBAA Sheet 01.

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

DATE: May 20/10 SERVICE BULLETIN No.: A330-53-3185

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**CONF 002

(1) Subtask 533185-832-001-001 - Do a Special Detailed Inspection of LH Frame 39.1

Work Zones and Access Panels

Zone Access/Work location

130 Work location Frame 39.1

Stringer 28

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills NON DESTRUCTIVE

TESTING

References

Non Destructive Test Manual (NTM) 53-31-05

Fig. A-FBAAA

Area to be Inspected

Sheet 01

Fig. A-FBBAA

Flow Chart

Sheet 01

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

(b) Do a special detailed inspection of the LH Frame 39.1 at hole area just above

stringer 28 as per NTM 53-31-05.

Refer to Fig. A-FBBAA Sheet 01.

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

(2) Subtask 533185-832-002-001 - Do a Special Detailed Inspection of RH Frame 39.1

Work Zones and Access Panels

Zone Access/Work location

130 Work location Frame 39.1

Stringer 28

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills NON DESTRUCTIVE

TESTING

References

Non Destructive Test Manual (NTM) 53-31-05

DATE: May 20/10 SERVICE BULLETIN No.: A330-53-3185

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SERVICE BULLETIN

References

Fig. A-FBAAA

Area to be Inspected

Sheet 01

Fig. A-FBBAA

Flow Chart

Sheet 01

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

(b) Do a special detailed inspection of the RH Frame 39.1 at hole area just above

stringer 28 as per NTM 53-31-05.

Refer to Fig. A-FBBAA Sheet 01.

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

**CONF ALL

D. TEST

**CONF 001

None

**CONF 002

None

**CONF ALL

E. CLOSE-UP

**CONF 001

(1) Subtask 533185-942-001-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

References

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

Task 25-52-00-400-801

Task 52-30-00-410-801

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

equipment.

(b) Install the insulation blankets.

(c) Install the sidewall panels 131AX and 132AX(Refer to AMM 06-41-53, Page Block

001 and AMM Task 25-52-00-400-801).

(d) Install the partition panels 131DX and 132DX(Refer to AMM 06-41-53, Page Block

001 and AMM Task 25-52-00-400-801).

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SERVICE BULLETIN

(e) If removed, install the ceiling panels 131VC and 132VC(Refer to AMM 06-41-53,

Page Block 001 and AMM Task 25-52-00-400-801).

(f) Remove the access platform(s).

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

52-30-00-410-801).

(h) Restore the systems and the aircraft to normal operating conditions.

**CONF 002

(1) Subtask 533185-942-001-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

References

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

Task 25-52-00-400-801

Task 52-30-00-410-801

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

equipment.

(b) Install the insulation blankets.

(c) Install the sidewall panels 131AX and 132AX(Refer to AMM 06-41-53, Page Block

001 and AMM Task 25-52-00-400-801).

(d) Install the partition panels 131DX and 132DX(Refer to AMM 06-41-53, Page Block

001 and AMM Task 25-52-00-400-801).

(e) If removed, install the ceiling panels 131VC and 132VC(Refer to AMM 06-41-53,

Page Block 001 and AMM Task 25-52-00-400-801).

(f) Remove the access platform(s).

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

52-30-00-410-801).

(h) Restore the systems and the aircraft to normal operating conditions.

DATE: May 20/10 SERVICE BULLETIN No.: A330-53-3185

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SERVICE BULLETIN

**CONF ALL

FITTING INSPECTION AREA

AREA TO BE INSPECTED

NOTE:

A

A

A

FR39.1

A A

LH SIDE SHOWN

RH SIDE SYMMETRICAL

A

G_SB_533185_5_BAAA_01_02

FITTING

MEMBER−ARCH

STGR28

STGR29

STGR30

Figure A-FBAAA - Sheet 01

Area to be Inspected

DATE: May 20/10 SERVICE BULLETIN No.: A330-53-3185

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SERVICE BULLETIN

**CONF ALL

QUESTION

ACTION

FINDING

AT THRESHOLD GIVEN IN PLANNING

INFORMATION PARAGRAPH E.(2).

YES CRACK NO

RE−INSPECT PER SPECIAL DETAILED

INSPECTION OF THE LH AND RH FRAME

DO A SPECIAL DETAILED INSPECTION OF THE LH AND RH FRAME 39.1

AT HOLE AREA JUST ABOVE STRINGER 28 AS PER NTM 53−31−05

CONTACT AIRBUS AND FOLLOW

THEIR CORRECTIVE ACTION

SEND TO AIRBUS THE

BEFORE NEXT FLIGHT 39.1 AT HOLE AREA JUST ABOVE 

INSPECTION REPORT

REFER TO APPENDIX 01

SEND TO AIRBUS THE

INSPECTION REPORT

REFER TO APPENDIX 01

G_SB_533185_5_BBAA_01_02

STRINGER 28 AS PER NTM 53−31−05

AT INTERVAL GIVEN IN PLANNING

INFORMATION PARAGRAPH E.(2).

Figure A-FBBAA - Sheet 01

Flow Chart

DATE: May 20/10 SERVICE BULLETIN No.: A330-53-3185

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This Page Intentionally Left Blank

DATE: May 20/10 SERVICE BULLETIN No.: A330-53-3185

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SERVICE BULLETIN

Appendix 01

**CONF ALL

(1) The result 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: May 20/10 SERVICE BULLETIN No.: A330-53-3185

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SERVICE BULLETIN

Appendix 01

**CONF ALL

SERVICE BULLETIN No. :

A/C MSN :

FLIGHT CYCLES :

FLIGHT HOURS :

A330−53−3185

DATE OF INSPECTION :

INSPECTION METHOD : SPECIAL DETAILED

INSPECTION

INSPECTION REPORT

CRACK AT HOLE AREA ABOVE STRINGER 28 AT FR39.1

LH SIDE RH SIDE

YES

NO

G_SB_533185_5_AAAA_01_01

(1)

(1) PROVIDE A CLEAR SKETCH SHOWING THE EXACT POSITION AND DIMENSION OF THE CRACK.

Figure A-FAAAA - Sheet 01

Inspection Report

DATE: May 20/10 SERVICE BULLETIN No.: A330-53-3185

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SERVICE BULLETIN

Appendix 02

**CONF ALL

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

more suitable for them.

DATE: May 20/10 SERVICE BULLETIN No.: A330-53-3185

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SERVICE BULLETIN

Appendix 02

**CONF ALL

ELAPSED TIME ASSUMPTIONS SERVICE BULLETIN No. A330−53−3185

ELAPSED TIME

(HOURS)

NOTE: THIS CHART IS ONLY A PROPOSAL.

OPERATORS MAY DETERMINE THAT ANOTHER WAY

TO DO THE WORK IS MORE SUITABLE FOR THEM.

MH ET PER

MH:

ET:

PER:

MANHOURS

ELAPSED TIME

NUMBER OF PERSONS

TOTAL MANHOURS (MH)

ELAPSED TIME (ET)

14.50

8.50

STEPS

0 5

5.00 3.00 2

INSPECTION OF FRAME 39.1 LH SIDE 1.00 1.00 1

GET ACCESS

10

CLOSE−UP 7.00 4.00 2

TEST 0.50 0.50 1

G_SB_533185_5_ABAA_01_00

INSPECTION OF FRAME 39.1 RH SIDE 1.00 1.00 1

Figure A-FABAA - Sheet 01

Elapsed Time Assumptions

DATE: May 20/10 SERVICE BULLETIN No.: A330-53-3185

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REPORTING SHEET

TITLE: FUSELAGE - CENTER FUSELAGE - INSPECTION OF FUSELAGE

INTERNAL STRUCTURE, FASTENER HOLE AREA ABOVE STRINGER

28 AT FRAME 39.1 WEB JUNCTION ON HOIST FITTING, LH/RH

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: May 20/10 SERVICE BULLETIN No.: A330-53-3185

REVISION No.: 00 - May 20/10 Page: 1

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SERVICE BULLETIN

QUALITY PERCEPTION FORM

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

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

improve the quality of our Service Bulletins.

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

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

- Quality rating of this SB 4 3 2 1

- Quality rating of the Accomplishment Instructions 4 3 2 1

- Quality rating of the Illustrations 4 3 2 1

- Is this SB easy to understand ? Y / N

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

short description of the issue.

Planning Material Instructions

X Effectivity X Kit content X Preparation

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

X Manpower X Industry support X Test

X References X Re-identification X Close-Up

X Publication X Tooling X Illustrations

Comments:

Operator: Date:

Name/Title:

Please return this form to:

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX FRANCE

Attn : SEM4 Service Bulletins Management

FAX : (33) 5 61 93 42 51

Or via your Resident Customer Support Office.

DATE: May 20/10 SERVICE BULLETIN No.: A330-53-3185

REVISION No.: 00 - May 20/10 Page: 1

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