@A318/A319/A320/A321

SERVICE BULLETIN

SUMMARY

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX

FRANCE

Tel : (33) 5 61 93 33 33

Telex : AIRBU 530526F

Fax : (33) 5 61 93 42 51

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

ATA SYSTEM: 53

TITLE: FUSELAGE - NOSE FORWARD FUSELAGE - INSPECTION OF MISSING

FASTENER AND DRILLING AT FR 24 STRG 39 RH SIDE.

**CONF ALL

MODIFICATIONS

None

REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

During a customer inspection in Final Assembly Line (FAL), one fastener was found missing at Frame

24, Stringer 39 RH side.

The hole of the missing fastener was not drilled.

A quality investigation has revealed that a fastener is possibly missing on a batch of in-service aircraft.

After checking that the fastener is missing, this Service Bulletin calls for the inspection of the fasteners

holes surrounding the missing one at Frame 24 Stringer 39 RH side, installation of oversized fasteners,

drilling of the missing hole and installation of the missing fastener.

Accomplishment of this Service Bulletin will contribute to ensure the structural integrity of the aircraft.

GENERAL EVALUATION

EVALUATION TABLE

COMPLIANCE RECOMMENDED (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 recommended to be accomplished to prevent significant operational

disruptions.

DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242

REVISION No.: 00 - May 22/12 Page: 1

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SERVICE BULLETIN

SUMMARY

MATERIAL PRICE INFORMATION

**CONF 001

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Kit 531242A01R01 1 1,900.00 Bolt, nut, rivet

**CONF 002

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Kit 531242A02R01 1 1,904.00 Bolt, nut, rivet

EFFECTIVITY

**CONF ALL

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

08U 31X 74T AAF AAW ADR AFL AVA BAW BEL CHH CSA CSC

CSN DLH EZY FFT GWI IAC LJB ONE PJS SLK TAM TJS

CONCURRENT REQUIREMENTS

None

REFERENCES / REPERCUSSIONS

TFU None

OEB None

AOT None

SIL None

LINE MAINTENANCE AFFECTED No

LIFE LIMIT None

OTHER None

NATURE OF THE WORK

AIRCRAFT YES

EQUIPMENT NO

HARD NO

SOFT NO

OBRM NO

DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242

REVISION No.: 00 - May 22/12 Page: 2

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SERVICE BULLETIN

SUMMARY

MANPOWER

**CONF 001

Task 531242-832-801-001: Inspection

TOTAL MANHOURS 26.00

ELAPSED TIME (HOURS) 26.00

**CONF 002

Task 531242-832-801-001: Inspection

TOTAL MANHOURS 26.00

ELAPSED TIME (HOURS) 26.00

APPENDICES

**CONF ALL

Appendix 01 - Inspection Report

DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242

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SERVICE BULLETIN

SUMMARY

**CONF ALL

Z130

A

FR24

FR34

A

ZONE TO BE INSPECTED

F

W

D B

B

FR24

STGR39

N_SB_531242_5_SAAA_01_00

Figure A-FSAAA - Sheet 01

DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242

REVISION No.: 00 - May 22/12 Page: 4

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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

ATA SYSTEM: 53

TITLE: FUSELAGE - NOSE FORWARD FUSELAGE - INSPECTION OF MISSING

FASTENER AND DRILLING AT FR 24 STRG 39 RH SIDE.

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

318-112 319-111 319-112 319-115 319-132 319-133

(2) Effectivity by MSN

3983 3985 3998 4000 4004 4007 4018 4020 4029 4036 4038-4040 4048 4052 4056

4069 4071 4076 4080 4087 4089 4121 4125 4127 4129 4132 4141 4151 4163-4164

4166 4169 4171 4182 4192 4200 4204 4211 4215 4222 4227-4228 4254 4256

4258-4259 4262 4268 4275 4282 4285 4287 4301 4313 4319 4327 4332 4336

(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

08U 4151

31X 4319

74T 4228

AAF 4268

DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242

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SERVICE BULLETIN

OPERATOR MSN

AAW 4004

ADR 4282 4301

AFL 3998

AVA 4200

BAW 4007 4039

BEL 4275

CHH 4262

CSA 4258

CSC 4018

CSN 3983 4036 4038 4071

DLH 4141 4182 4332

EZY 4040 4048 4056 4069 4076 4080 4087 4125 4129 4132 4313 4327

FFT 4127 4204 4254

GWI 4166 4227 4256 4285

IAC 4020 4029 4052 4089 4121 4164

LJB 3985

ONE 4222 4287 4336

PJS 4211

SLK 4215 4259

TAM 4000 4163 4171 4192

TJS 4169

(4) Configuration by MSN

MSN CONFIGURATION

3983 3998 4000 4004 4018 4020 4029 4036 4038 4040 4048

4052 4056 4069 4071 4076 4080 4087 4089 4121 4125 4127

4129 4132 4141 4151 4163 4164 4166 4171 4182 4192 4200

4204 4215 4222 4227 4228 4254 4256 4258 4259 4262 4268

4275 4282 4285 4287 4301 4313 4319 4327 4332 4336

001

3985 4007 4039 4169 4211 002

(5) Configuration definition

**CONF 001

Config. 001 is valid for A319 aircraft.

**CONF 002

Config. 002 is valid for A318 aircraft.

(6) Material Effectivity

**CONF 001

MATERIAL QTY PER A/C SEE NOTES

Kit 531242A01R01 1

Consumable CMLA01 1

DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242

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SERVICE BULLETIN

**CONF 002

MATERIAL QTY PER A/C SEE NOTES

Kit 531242A02R01 1

Consumable CMLA01 1

**CONF ALL

B. CONCURRENT REQUIREMENTS

None

C. REASON

(1) History

During a customer inspection in Final Assembly Line (FAL), one fastener was found

missing at Frame 24, Stringer 39 RH side.

The hole of the missing fastener was not drilled.

A quality investigation has revealed that a fastener is possibly missing on a batch of inservice aircraft.

(2) Objective/Action

After checking that the fastener is missing, this Service Bulletin calls for the inspection of

the fasteners holes surrounding the missing one at Frame 24 Stringer 39 RH side,

installation of oversized fasteners, drilling of the missing hole and installation of the

missing fastener.

(3) Advantages

Accomplishment of this Service Bulletin will contribute to ensure the structural integrity of

the aircraft.

(4) Operational/Maintenance Consequences

None

D. DESCRIPTION

To accomplish this Service Bulletin it is necessary to :

**CONF 001

Task 531242-832-801-001: Inspection

(1) Do a Detailed Inspection for the missing fastener at nose forward fuselage at Fr 24

Strg 39 (RH Side)

(2) Remove the 5 surrounding fasteners at frame 24 stringer 39

DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242

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SERVICE BULLETIN

(3) Do the inspection of the 5 holes of the removed fasteners

(4) Drill one hole in the structure and the fitting and install the new fasteners in the

inspected holes

**CONF 002

Task 531242-832-801-001: Inspection

(1) Do a Detailed Inspection for the missing fastener at nose forward fuselage at Fr 24

Strg 39 (RH Side)

(2) Remove the 5 surrounding fasteners at frame 24 stringer 39

(3) Do the inspection of the 5 holes of the removed fasteners

(4) Drill one hole in the structure and the fitting and install the new fasteners in the

inspected holes

**CONF ALL

E. COMPLIANCE

(1) Classification

RECOMMENDED: Service Bulletin recommended to be accomplished to prevent

significant operational disruptions.

(2) Accomplishment Timescale

Accomplishment of this Service Bulletin is recommended:

- Before accumulation of 5,000FC (Flight Cycles) since first flight for A319 and A318

PRE-MOD 39195 or within 4,300FC from SB issue date whichever occurs later.

- Before accumulation of 3,000FC since first flight for A318 POST-MOD 39195 (Elite)

or A318 POST SB A320-00-1219.

- Before accumulation of 2,500FC since first flight for A319 operated as CJ (POSTMOD 28238 , 28162 and 28342).

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/or intervals

and/or date) given above but reference should be made to the AD for confirmation of the

mandated accomplishment timescale.

F. APPROVAL

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

DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242

REVISION No.: 00 - May 22/12 Page: 4

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

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

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

before incorporation of the Service Bulletin.

G. MANPOWER

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

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

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

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

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

included.

**CONF 001

Task 531242-832-801-001: Inspection

Get Access 3.00

On Aircraft

Do a Detailed Inspection for the missing fastener at

nose forward fuselage at Fr 24 Strg 39 (RH Side)

6.00

Remove the 5 surrounding fasteners at frame 24

stringer 39

0.50

Do the inspection of the 5 holes of the removed

fasteners

1.50

Drill one hole in the structure and the fitting and install

the new fasteners in the inspected holes

1.25

Close-Up 13.75

TOTAL MANHOURS 26.00

ELAPSED TIME (HOURS) 26.00

NOTE: Operators have to consider as a maximum 3.00 hours of Get Access in case

that the fastener is not missing.

Operators have to consider as a maximum 9.00 hours of Get Access in case

that the fastener is missing.

**CONF 002

Task 531242-832-801-001: Inspection

Get Access 3.00

On Aircraft

Do a Detailed Inspection for the missing fastener at

nose forward fuselage at Fr 24 Strg 39 (RH Side)

6.00

Remove the 5 surrounding fasteners at frame 24

stringer 39

0.50

Do the inspection of the 5 holes of the removed

fasteners

1.50

Drill one hole in the structure and the fitting and install

the new fasteners in the inspected holes

1.25

DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242

REVISION No.: 00 - May 22/12 Page: 5

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Task 531242-832-801-001: Inspection

Close-Up 13.75

TOTAL MANHOURS 26.00

ELAPSED TIME (HOURS) 26.00

NOTE: Operators have to consider as a maximum 3.00 hours of Get Access in case

that the fastener is not missing.

Operators have to consider as a maximum 9.00 hours of Get Access in case

that the fastener is missing.

**CONF ALL

H. WEIGHT AND BALANCE

Not Changed

I. ELECTRICAL LOAD DATA

Not Changed

J. REFERENCES

**CONF 001

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

25-54-11 52-30-00 53-12-14

53-22-14

Consumable Material List (CML)

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

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

Service Bulletin (SB) A320-00-1219

Standards Manual (SM)

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

51-42-11 51-43-00 51-44-00

51-46-00 51-47-00 51-75-12

**CONF 002

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

25-54-11 52-30-00 53-12-14

53-22-14

Consumable Material List (CML)

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

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

Service Bulletin (SB) A320-00-1219

Standards Manual (SM)

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

51-42-11 51-43-00 51-44-00

51-46-00 51-47-00 51-75-12

DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242

REVISION No.: 00 - May 22/12 Page: 6

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SERVICE BULLETIN

**CONF ALL

K. PUBLICATION AFFECTED

None

L. INTERCHANGEABILITY/MIXABILITY

Not Applicable

M. SPARES

None

DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242

REVISION No.: 00 - May 22/12 Page: 7

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This Page Intentionally Left Blank

DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242

REVISION No.: 00 - May 22/12 Page: 8

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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 531242A01R01

Kit 531242A02R01

AIRBUS Material, Logistics and Suppliers

Weg beim Jaeger 150

D-22335 Hamburg

GERMANY

For ordering by internet:

http://spares.airbus.com

For ordering by fax: +49 40 50 76 25 90

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

(2) Price and Availability

Kit 531242A01R01

Cost 1,900.00 USD

Availability 90 calendar days from receipt of order

Kit 531242A02R01

Cost 1,904.00 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

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

C. LIST OF COMPONENTS

Kit 531242A01R01

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

NOTES

3 ASNA2528-3 30 Nut

8 NSA5057-4 5 Nut

13 ASNA2049DXJ4820 3 Rivet

DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242

REVISION No.: 00 - May 22/12 Page: 9

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

NOTES

14 EN6114V3-7 1 Bolt

15 ASNA2050DXJ4820 2 Rivet

16 EN6114V3X7 5 Bolt

17 EN6115V3X4 19 Bolt

18 EN6114V3X5 2 Bolt

19 EN6114V4X9 9 Bolt

30 ASNA2528-4 9 Nut

41 EN6115V3X6 1 Bolt

60 EN6114V3X3 1 Bolt

70 EN6114V3X4 1 Bolt

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

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

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

to part number relationship.

Kit 531242A02R01

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

NOTES

3 ASNA2528-3 31 Nut

8 NSA5057-4 5 Nut

13 ASNA2049DXJ4820 3 Rivet

14 EN6114V3-7 1 Bolt

15 ASNA2050DXJ4820 2 Rivet

16 EN6114V3X7 6 Bolt

17 EN6115V3X4 19 Bolt

18 EN6114V3X5 2 Bolt

19 EN6114V4X9 8 Bolt

30 ASNA2528-4 8 Nut

41 EN6115V3X6 1 Bolt

60 EN6114V3X3 1 Bolt

70 EN6114V3X4 1 Bolt

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

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

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

to part number relationship.

D. LIST OF MATERIALS - OPERATOR SUPPLIED

(1) Consumable Materials

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO CML

MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242

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ITEM DESCRIPTION REFERENCE TO CML

MAT. No.

QTY PER A/C SEE

NOTES

Corrosion Inhibitingfillet Consistency 09-016 As required

Cleaning Solvent 11-003 As required

Cleaning Solvent 11-010 As required

Cleaning Solvent 11-016 As required

Cleaning Solvent 11-026 As required

Corrosion Preventive temporary

Protective compound

15-007 As required

Anti-Corrosion Primer 16-001 As required

Polyurethane Finish Paint 16-018 As required

Flexible Polyurethane 16-021 As required

(2) Components

None

(3) Equipment

None

E. PARTS TO BE RE-IDENTIFIED BY OPERATOR

None

F. TOOLING

None

DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242

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DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242

REVISION No.: 00 - May 22/12 Page: 12

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3. ACCOMPLISHMENT INSTRUCTIONS

Task 531242-832-801-001 - 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.

IF THERE IS CONTAMINATION, ESPM 20-55-00.

Task Associated Data

**CONF 001

Zone

130

Modified FIN

131AF 131CW 132GG 132MF 131PG

Manpower

TOTAL MANHOURS 26.00

ELAPSED TIME (HOURS) 26.00

**CONF 002

Zone

130

Modified FIN

131AF 131CW 132GG 132MF 131PG

Manpower

TOTAL MANHOURS 26.00

ELAPSED TIME (HOURS) 26.00

DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242

REVISION No.: 00 - May 22/12 Page: 13

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**CONF ALL

A. GENERAL

**CONF 001

(1) Subtask 531242-910-002-001 - 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

Sealant-Brush Consistency 09-013 As required

Corrosion Inhibitingfillet

Consistency

09-016 As required

Corrosion Preventive

temporary Protective

compound

15-007

Anti-Corrosion Primer 16-001 As required

Polyurethane Finish Paint 16-018 As required

References

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

06-31-53, Page Block 001

Consumable Material List (CML)

Structural Repair Manual (SRM) 51-24-00

51-24-12

51-42-00

51-42-11

51-43-00

51-44-00

51-46-00

51-47-00

51-75-12

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

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

(c) Remove and install the fasteners (Refer to SRM 51-42-11).

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

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

(f) For the space and margin of the fasteners (Refer to SRM 51-47-00).

DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242

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

(h) For the specification of the material numbers (Mat No.), refer to CML.

(i) Repair of the paint coating (Refer to SRM 51-75-12).

(j) For the countersinking (Refer to SRM 51-46-00).

(k) During the installation of the fasteners apply:

Sealant-Brush

Consistency

09-013 As required

(l) After the installation of the fasteners apply:

Anti-Corrosion

Primer

16-001 As required

Polyurethane Finish

Paint

16-018 As required

(m) Between the fitting and the structure, apply:

Corrosion

Inhibitingfillet

Consistency

09-016 As required

(n) Perform reprotection of the reworked areas as per SRM 51-24-12.

(o) Perform protection of reworked areas with:

Corrosion

Preventive

temporary

Protective

compound

15-007 As required

(2) Subtask 531242-839-003-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

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

Service Bulletin.

**CONF 002

(1) Subtask 531242-910-002-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242

REVISION No.: 00 - May 22/12 Page: 15

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Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

Corrosion Inhibitingfillet

Consistency

09-016 As required

Corrosion Preventive

temporary Protective

compound

15-007

Anti-Corrosion Primer 16-001 As required

Polyurethane Finish Paint 16-018 As required

References

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

06-31-53, Page Block 001

Consumable Material List (CML)

Structural Repair Manual (SRM) 51-24-00

51-24-12

51-42-00

51-42-11

51-43-00

51-44-00

51-46-00

51-47-00

51-75-12

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

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

(c) Remove and install the fasteners (Refer to SRM 51-42-11).

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

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

(f) For the space and margin of the fasteners (Refer to SRM 51-47-00).

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

(h) For the specification of the material numbers (Mat No.), refer to CML.

(i) Repair of the paint coating (Refer to SRM 51-75-12).

(j) For the countersinking (Refer to SRM 51-46-00).

DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242

REVISION No.: 00 - May 22/12 Page: 16

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(k) During the installation of the fasteners apply:

Sealant-Brush

Consistency

09-013 As required

(l) After the installation of the fasteners apply:

Anti-Corrosion

Primer

16-001 As required

Polyurethane Finish

Paint

16-018 As required

(m) Between the fitting and the structure, apply:

Corrosion

Inhibitingfillet

Consistency

09-016 As required

(n) Perform reprotection of the reworked areas as per SRM 51-24-12.

(o) Perform protection of reworked areas with:

Corrosion

Preventive

temporary

Protective

compound

15-007 As required

(2) Subtask 531242-839-003-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

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

Service Bulletin.

**CONF ALL

B. PREPARATION

**CONF 001

(1) Subtask 531242-941-002-001 - Job Set-up

Work Zones and Access Panels

Zone Access/Work location

130

Manpower Resources

Skills NON SPECIFIC

DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242

REVISION No.: 00 - May 22/12 Page: 17

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SERVICE BULLETIN

References

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

Task 25-54-11-000-001

Task 52-30-00-860-001

Task 53-22-14-000-001

Fig. A-FBDAA

Removal and Installation of the Fitting

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Fig. A-FBEAA

Removal and installation of the sealant

Sheet 01

Sheet 02

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

(b) Open the forward cargo door 825AR (Refer to AMM Task 52-30-00-860-001).

(c) Remove the FWD cargo-compartment panel FIN 131CW (Refer to AMM 06-41-53,

Page Block 001 and AMM Task 25-54-11-000-001).

(d) If the fastener is missing, remove the panels FIN 131AF or FIN 131PG or FIN

132GG or FIN 132MF (Refer to AMM Task 53-22-14-000-001 and AMM 06-41-53,

Page Block 001).

**CONF 002

(1) Subtask 531242-941-002-002 - Job Set-up

Work Zones and Access Panels

Zone Access/Work location

130

Manpower Resources

Skills NON SPECIFIC

References

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

Task 25-54-11-000-001

Task 52-30-00-860-001

Task 53-22-14-000-001

Fig. A-FBEAA

Removal and installation of the sealant

Sheet 01

Sheet 02

Fig. A-FBDAB

Removal and Installation of the Fitting

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

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

(b) Open the forward cargo door 825AR (Refer to AMM Task 52-30-00-860-001).

DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242

REVISION No.: 00 - May 22/12 Page: 18

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(c) Remove the FWD cargo-compartment panel FIN 131CW (Refer to AMM 06-41-53,

Page Block 001 and AMM Task 25-54-11-000-001).

(d) If the fastener is missing, remove the panels FIN 131AF or FIN 131PG or FIN

132GG or FIN 132MF (Refer to AMM Task 53-22-14-000-001 and AMM 06-41-53,

Page Block 001).

**CONF ALL

C. PROCEDURE

NOTE: 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 fasteners grip length in accordance with SRM

Chapter 51.

**CONF 001

(1) Subtask 531242-832-001-001 - Do a Detailed Inspection for the missing fastener at

nose forward fuselage at Fr 24 Strg 39 (RH Side)

Manpower Resources

Manhours 6.00

Minimum number of person 1

Subtask elapsed time 6.00

Skills AIRFRAME

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Cleaning Solvent 11-003

Cleaning Solvent 11-010

Cleaning Solvent 11-016

Cleaning Solvent 11-026

References

Consumable Material List (CML)

Fig. A-FBEAA

Removal and installation of the sealant

Sheet 01

Sheet 02

Fig. A-FBDAA

Removal and Installation of the Fitting

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242

REVISION No.: 00 - May 22/12 Page: 19

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References

Fig. A-FBAAA

Inspection of the surrounding holes and

area to be inspected

Sheet 01

Sheet 02

Sheet 03

Fig. A-FFAAA

Flow Chart

Sheet 01

(a) At the threshold given in the planning information paragraph E.(2):

1 Do a detailed inspection for the missing fastener at nose forward fuselage at

Frame 24 string 39 (RH Side).

Refer to Fig. A-FBAAA Sheet 01, Fig. A-FBAAA Sheet 02, Fig. A-FBAAA

Sheet 03 and Fig. A-FFAAA Sheet 01

2 If the fastener is missing:

a Remove the sealant from the lower area of the cargo door.

<1> Remove:

Refer to Fig. A-FBEAA Sheet 01

Flexible Polyurethane 16-021

Corrosion Inhibiting

fillet Consistency

09-016

with:

Cleaning Solvent 11-016 As required

or

Cleaning Solvent 11-003 As required

or

Cleaning Solvent 11-010 As required

or

Cleaning Solvent 11-026 As required

b Remove fitting for access

Refer to Fig. A-FBDAA Sheet 01 thru Fig. A-FBDAA Sheet 05

<1> Remove:

1 Fitting Item (40) Retain

attached with:

DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242

REVISION No.: 00 - May 22/12 Page: 20

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SERVICE BULLETIN

2 Rivet ASNA2050DEJ4020 Item (1) Discard

4 Bolt ASNA2026V3-7 Item (2) Discard

4 Nut ASNA2528-3 Item (3) Discard

19 Bolt ASNA2027V3-4 Item (4) Discard

1 Bolt ASNA2027V3-6 Item (100) Discard

20 Nut ASNA2528-3 Item (3) Discard

2 Bolt ASNA2026V3-5 Item (5) Discard

2 Nut ASNA2528-3 Item (3) Discard

1 Bolt ASNA2026V3-7 Item (2) Discard

1 Nut ASNA2528-3 Item (3) Discard

9 Bolt ASNA2026V4-9 Item (6) Discard

9 Nut ASNA2528-4 Item (30) Discard

2 Bolt MS21250-04006 Item (7) Retain

2 Nut NSA5057-4 Item (8) Discard

3 Bolt MS21250-04004 Item (9) Retain

3 Nut NSA5057-4 Item (8) Discard

NOTE: The removal of this fitting will allow the access to the

modification zone.

c Do SUBTASK 531242-020-002 001 Remove the 5 surrounding fasteners

at frame 24 stringer 39 .

d Do SUBTASK 531242-220-001 001 Do the inspection of the 5 holes of

the removed fasteners .

3 If the fastener is not missing, no further action is needed.

4 Send Inspection Report to Airbus.

DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242

REVISION No.: 00 - May 22/12 Page: 21

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(2) Subtask 531242-020-002-001 - Remove the 5 surrounding fasteners at frame 24

stringer 39

Work Zones and Access Panels

Zone Access/Work location

130 Work location from Frame 24 to Frame 24A

Stringer 39

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

References

Fig. A-FBAAA

Inspection of the surrounding holes and

area to be inspected

Sheet 01

Sheet 02

Sheet 03

(a) Remove:

Refer to Fig. A-FBAAA Sheet 01 thru Fig. A-FBAAA Sheet 03

3 Rivet ASNA2049DXJ4020 Item (10) Discard

1 Rivet EN6100P040A040G Item (11) Discard

1 Rivet EN6100P040A030G Item (50) Discard

2 Collar EN6051-040A Item (12) Discard

(3) Subtask 531242-220-001-001 - Do the inspection of the 5 holes of the removed

fasteners

Work Zones and Access Panels

Zone Access/Work location

130 Work location from Frame 24 to Frame 24A

Stringer 39

Manpower Resources

Manhours 1.50

Minimum number of person 1

Subtask elapsed time 1.50

Skills AIRFRAME

References

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

DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242

REVISION No.: 00 - May 22/12 Page: 22

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References

Fig. A-FBAAA

Inspection of the surrounding holes and

area to be inspected

Sheet 01

Sheet 02

Sheet 03

Fig. A-FFAAA

Flow Chart

Sheet 01

(a) Do a check of the 5 hole diameters of the removed fasteners. Fig. A-FBAAA Sheet

03 for diameter values.

1 If the diameter is not correct, contact AIRBUS and apply corrective action

before next flight.

2 If the diameter is correct, do the following instructions:

a For the inspection area, Fig. A-FBAAA Sheet 01 thru Fig. A-FBAAA

Sheet 03.

b Do a rototest inspection of the 5 holes of the removed fasteners as per

NTM 51-10-01 part 6 procedure A, refer to Fig. A-FFAAA Sheet 01.

<1> If crack found, contact AIRBUS and apply corrective action before

next flight.

<2> If no crack found, do SUBTASK 531242-420-003 001 Drill one hole

in the structure and the fitting and install the new fasteners in the

inspected holes .

c For the inspection report, refer to Appendix 01 - Inspection Report .

(4) Subtask 531242-420-003-001 - Drill one hole in the structure and the fitting and

install the new fasteners in the inspected holes

Work Zones and Access Panels

Zone Access/Work location

130

Manpower Resources

Manhours 1.25

Minimum number of person 1

Subtask elapsed time 1.25

Skills AIRFRAME

Material necessary to do the job

Kit 531242A01R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

3 ASNA2528-3 2 Nut

13 ASNA2049DXJ4820 3 Rivet

60 EN6114V3X3 1 Bolt

DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242

REVISION No.: 00 - May 22/12 Page: 23

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ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

70 EN6114V3X4 1 Bolt

References

Fig. A-FBCAA

Installation of the fasteners

Sheet 01

Sheet 02

Sheet 03

Sheet 04

(a) Oversize the 5 inspected holes on the structure at FR24, STGR39 to the

dimensions given in Fig. A-FBCAA Sheet 03.

(b) Drill 1 hole on the structure at FR24, STGR39 to the dimensions given in Fig. AFBCAA Sheet 03.

NOTE: Drill the hole from the outside of the aircraft.

(c) Temporarily put the fitting Item (40) in position.

(d) Counterdrill one hole in the fitting Item (40).

(e) Remove the fitting Item (40) and deburr the hole.

(f) Wet install with sealant:

3 Rivet ASNA2049DXJ4820 Item 13

1 Bolt EN6114V3X3 Item 60

1 Bolt EN6114V3X4 Item 70

2 Nut ASNA2528-3 Item 3

**CONF 002

(1) Subtask 531242-832-001-002 - Do a Detailed Inspection for the missing fastener at

nose forward fuselage at Fr 24 Strg 39 (RH Side)

Manpower Resources

Manhours 6.00

Minimum number of person 1

Subtask elapsed time 6.00

Skills AIRFRAME

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Cleaning Solvent 11-003

DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242

REVISION No.: 00 - May 22/12 Page: 24

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ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Cleaning Solvent 11-010

Cleaning Solvent 11-016

Cleaning Solvent 11-026

References

Consumable Material List (CML)

Fig. A-FBEAA

Removal and installation of the sealant

Sheet 01

Sheet 02

Fig. A-FBDAB

Removal and Installation of the Fitting

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Fig. A-FBAAA

Inspection of the surrounding holes and

area to be inspected

Sheet 01

Sheet 02

Sheet 03

Fig. A-FFAAB

Flow Chart

Sheet 01

(a) At the threshold given in the planning information paragraph E.(2):

1 Do a detailed inspection for the missing fastener at nose forward fuselage at

Frame 24 string 39 (RH Side).

Refer to Fig. A-FBAAA Sheet 01, Fig. A-FBAAA Sheet 02, Fig. A-FBAAA

Sheet 03 and Fig. A-FFAAB Sheet 01

2 If the fastener is missing:

a Remove the sealant from the lower area of the cargo door.

<1> Remove:

Refer to Fig. A-FBEAA Sheet 01

Flexible Polyurethane 16-021

Corrosion Inhibiting

fillet Consistency

09-016

with:

Cleaning Solvent 11-016 As required

or

Cleaning Solvent 11-003 As required

or

DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242

REVISION No.: 00 - May 22/12 Page: 25

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Cleaning Solvent 11-010 As required

or

Cleaning Solvent 11-026 As required

b Remove fitting for access

Fig. A-FBDAB Sheet 01 thru Fig. A-FBDAB Sheet 05

<1> Remove:

1 Fitting Item (40) Retain

attached with:

2 Rivet ASNA2050DEJ4020 Item (1) Discard

4 Bolt ASNA2026V3-7 Item (2) Discard

4 Nut ASNA2528-3 Item (3) Discard

19 Bolt ASNA2027V3-4 Item (4) Discard

1 Bolt ASNA2027V3-6 Item (100) Discard

20 Nut ASNA2528-3 Item (3) Discard

2 Bolt ASNA2026V3-5 Item (5) Discard

2 Nut ASNA2528-3 Item (3) Discard

1 Bolt ASNA2026V3-7 Item (2) Discard

1 Nut ASNA2528-3 Item (3) Discard

8 Bolt ASNA2026V4-9 Item (6) Discard

8 Nut ASNA2528-4 Item (30) Discard

1 Bolt EN6114V3-7 Item (14) Discard

1 Nut ASNA2528-3 Item (3) Discard

2 Bolt MS21250-04006 Item (7) Retain

2 Nut NSA5057-4 Item (8) Discard

3 Bolt MS21250-04004 Item (9) Retain

DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242

REVISION No.: 00 - May 22/12 Page: 26

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SERVICE BULLETIN

3 Nut NSA5057-4 Item (8) Discard

NOTE: The removal of this fitting will allow the access to the

modification zone.

c Do SUBTASK 531242-020-002 002 Remove the 5 surrounding fasteners

at frame 24 stringer 39 .

d Do SUBTASK 531242-220-001 003 Do the inspection of the 5 holes of

the removed fasteners .

3 If the fastener is not missing, no further action is needed.

4 Send Inspection Report to Airbus.

(2) Subtask 531242-020-002-002 - Remove the 5 surrounding fasteners at frame 24

stringer 39

Work Zones and Access Panels

Zone Access/Work location

130 Work location from Frame 24 to Frame 24A

Stringer 39

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

References

Fig. A-FBAAA

Inspection of the surrounding holes and

area to be inspected

Sheet 01

Sheet 02

Sheet 03

(a) Remove:

Refer to Fig. A-FBAAA Sheet 01 thru Fig. A-FBAAA Sheet 03

3 Rivet ASNA2049DXJ4020 Item (10) Discard

1 Rivet EN6100P040A040G Item (11) Discard

1 Rivet EN6100P040A030G Item (50) Discard

2 Collar EN6051-040A Item (12) Discard

DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242

REVISION No.: 00 - May 22/12 Page: 27

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(3) Subtask 531242-220-001-003 - Do the inspection of the 5 holes of the removed

fasteners

Work Zones and Access Panels

Zone Access/Work location

130 Work location from Frame 24 to Frame 24A

Stringer 39

Manpower Resources

Manhours 1.50

Minimum number of person 1

Subtask elapsed time 1.50

Skills AIRFRAME

References

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

Fig. A-FBAAA

Inspection of the surrounding holes and

area to be inspected

Sheet 01

Sheet 02

Sheet 03

Fig. A-FFAAB

Flow Chart

Sheet 01

(a) Do a check of the 5 hole diameters of the removed fasteners. Fig. A-FBAAA Sheet

03 for diameter values.

1 If the diameter is not correct, contact AIRBUS and apply corrective action

before next flight.

2 If the diameter is correct, do the following instructions:

a For the inspection area, Fig. A-FBAAA Sheet 01 thru Fig. A-FBAAA

Sheet 03.

b Do a rototest inspection of the 5 holes of the removed fasteners as per

NTM 51-10-01 part 6 procedure A, refer to Fig. A-FFAAB Sheet 01.

<1> If crack found, contact AIRBUS and apply corrective action before

next flight.

<2> If no crack found, do SUBTASK 531242-420-003 002 Drill one hole

in the structure and the fitting and install the new fasteners in the

inspected holes .

c For the inspection report, refer to Appendix 01 - Inspection Report .

(4) Subtask 531242-420-003-002 - Drill one hole in the structure and the fitting and

install the new fasteners in the inspected holes

Work Zones and Access Panels

Zone Access/Work location

130

DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242

REVISION No.: 00 - May 22/12 Page: 28

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Manpower Resources

Manhours 1.25

Minimum number of person 1

Subtask elapsed time 1.25

Skills AIRFRAME

Material necessary to do the job

Kit 531242A02R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

3 ASNA2528-3 2 Nut

13 ASNA2049DXJ4820 3 Rivet

60 EN6114V3X3 1 Bolt

70 EN6114V3X4 1 Bolt

References

Fig. A-FBCAA

Installation of the fasteners

Sheet 01

Sheet 02

Sheet 03

Sheet 04

(a) Oversize the 5 inspected holes on the structure at FR24, STGR39 to the

dimensions given in Fig. A-FBCAA Sheet 03.

(b) Drill 1 hole on the structure at FR24, STGR39 to the dimensions given in Fig. AFBCAA Sheet 03.

NOTE: Drill the hole from the outside of the aircraft.

(c) Temporarily put the fitting Item (40) in position.

(d) Counterdrill one hole in the fitting Item (40).

(e) Remove the fitting Item (40) and deburr the hole.

(f) Wet install with sealant:

3 Rivet ASNA2049DXJ4820 Item 13

1 Bolt EN6114V3X3 Item 60

1 Bolt EN6114V3X4 Item 70

2 Nut ASNA2528-3 Item 3

DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242

REVISION No.: 00 - May 22/12 Page: 29

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**CONF ALL

D. TEST

**CONF 001

None

**CONF 002

None

**CONF ALL

E. CLOSE-UP

**CONF 001

(1) Subtask 531242-010-001-001 - Install items removed for access (Only necessary

when the fastener was missing)

Manpower Resources

Skills AIRFRAME

Material necessary to do the job

Kit 531242A01R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

3 ASNA2528-3 28 Nut

8 NSA5057-4 5 Nut

14 EN6114V3-7 1 Bolt

15 ASNA2050DXJ4820 2 Rivet

16 EN6114V3X7 5 Bolt

17 EN6115V3X4 19 Bolt

18 EN6114V3X5 2 Bolt

19 EN6114V4X9 9 Bolt

30 ASNA2528-4 9 Nut

41 EN6115V3X6 1 Bolt

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Corrosion Inhibiting fillet

Consistency

09-016 As required

Flexible Polyurethane 16-021 As required

References

Consumable Material List (CML)

DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242

REVISION No.: 00 - May 22/12 Page: 30

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References

Fig. A-FBCAA

Installation of the fasteners

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Fig. A-FBEAA

Removal and installation of the sealant

Sheet 01

Sheet 02

Fig. A-FBDAA

Removal and Installation of the Fitting

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

(a) Install the removed fitting and the missing fastener.

1 Temporarily put in position the fitting Item (40).

2 Oversize the 38 holes on the structure and the fitting between FR24 and

FR25, STGR39 to the dimensions given in Fig. A-FBDAA Sheet 05.

3 Remove the fitting Item (40) and deburr the holes.

4 Wet install with sealant:

1 Fitting Item (40) Retained at

removal

attached with

2 Rivet ASNA2050DXJ4820 Item 15

4 Bolt EN6114V3X7 Item 16

4 Nut ASNA2528-3 Item 3

19 Bolt EN6115V3X4 Item 17

1 Bolt EN6115V3X6 Item 41

20 Nut ASNA2528-3 Item 3

2 Bolt EN6114V3X5 Item 18

2 Nut ASNA2528-3 Item 3

1 Bolt EN6114V3X7 Item 16

1 Nut ASNA2528-3 Item 3

9 Bolt EN6114V4X9 Item 19

9 Nut ASNA2528-4 Item 30

DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242

REVISION No.: 00 - May 22/12 Page: 31

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2 Bolt MS21250-04006 Item (7) Retained at

removal

2 Nut NSA5057-4 Item 8

3 Bolt MS21250-04004 Item (9) Retained at

removal

3 Nut NSA5057-4 Item 8

5 Install the missing fastener:

Fig. A-FBCAA Sheet 03

1 Bolt EN6114V3-7 Item 14

1 Nut ASNA2528-3 Item 3

(b) Install the sealant on the lower area of the cargo door.

1 Apply sealant on the lower area of the cargo door:

Fig. A-FBEAA Sheet 01 and Fig. A-FBEAA Sheet 02

a Do a block of:

Corrosion Inhibiting

fillet Consistency

09-016 As required

at dimensions given in Fig. A-FBEAA Sheet 02 and make it dry out.

b Over the block already cured, apply (Refer to Fig. A-FBEAA Sheet 02):

Corrosion Inhibiting

fillet Consistency

09-016 As required

c Do the protection with:

Flexible

Polyurethane

16-021 As required

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

equipment.

(2) Subtask 531242-942-002-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242

REVISION No.: 00 - May 22/12 Page: 32

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SERVICE BULLETIN

References

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

Task 25-54-11-400-001

Task 52-30-00-860-002

Task 53-12-14-400-001

Fig. A-FBDAA

Removal and Installation of the Fitting

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Fig. A-FBEAA

Removal and installation of the sealant

Sheet 01

Sheet 02

Fig. A-FBCAA

Installation of the fasteners

Sheet 01

Sheet 02

Sheet 03

Sheet 04

(a) Install the FWD cargo-compartment panel FIN 131CW (Refer to AMM 06-41-53,

Page Block 001 and AMM Task 25-54-11-400-001).

(b) Install the panels FIN 131AF or FIN 131PG or FIN 132GG or FIN 132MF (Refer to

AMM Task 53-12-14-400-001).

(c) Close the forward cargo-compartment door 825AR (Refer to AMM Task

52-30-00-860-002).

(d) Remove the access platform(s).

**CONF 002

(1) Subtask 531242-010-001-002 - Install items removed for access (Only necessary

when the fastener was missing)

Manpower Resources

Skills AIRFRAME

Material necessary to do the job

Kit 531242A02R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

3 ASNA2528-3 29 Nut

8 NSA5057-4 5 Nut

14 EN6114V3-7 1 Bolt

15 ASNA2050DXJ4820 2 Rivet

16 EN6114V3X7 6 Bolt

17 EN6115V3X4 19 Bolt

18 EN6114V3X5 2 Bolt

19 EN6114V4X9 8 Bolt

30 ASNA2528-4 8 Nut

41 EN6115V3X6 1 Bolt

DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242

REVISION No.: 00 - May 22/12 Page: 33

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Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Corrosion Inhibiting fillet

Consistency

09-016 As required

Flexible Polyurethane 16-021 As required

References

Consumable Material List (CML)

Fig. A-FBCAA

Installation of the fasteners

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Fig. A-FBEAA

Removal and installation of the sealant

Sheet 01

Sheet 02

Fig. A-FBDAB

Removal and Installation of the Fitting

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

(a) Install the removed fitting and the missing fastener.

1 Temporarily put in position the fitting Item (40).

2 Oversize the 38 holes on the structure and the fitting between FR24 and

FR25, STGR39 to the dimensions given in Fig. A-FBDAB Sheet 05.

3 Remove the fitting Item (40) and deburr the holes.

4 Wet install with sealant:

1 Fitting Item (40) Retained at

removal

attached with

2 Rivet ASNA2050DXJ4820 Item 15

4 Bolt EN6114V3X7 Item 16

4 Nut ASNA2528-3 Item 3

19 Bolt EN6115V3X4 Item 17

1 Bolt EN6115V3X6 Item 41

20 Nut ASNA2528-3 Item 3

2 Bolt EN6114V3X5 Item 18

2 Nut ASNA2528-3 Item 3

DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242

REVISION No.: 00 - May 22/12 Page: 34

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1 Bolt EN6114V3X7 Item 16

1 Nut ASNA2528-3 Item 3

8 Bolt EN6114V4X9 Item 19

8 Nut ASNA2528-4 Item 30

1 Bolt EN6114V3X7 Item 16

1 Nut ASNA2528-3 Item 3

2 Bolt MS21250-04006 Item (7) Retained at

removal

2 Nut NSA5057-4 Item 8

3 Bolt MS21250-04004 Item (9) Retained at

removal

3 Nut NSA5057-4 Item 8

5 Install the missing fastener:

Fig. A-FBCAA Sheet 03

1 Bolt EN6114V3-7 Item 14

1 Nut ASNA2528-3 Item 3

(b) Install the sealant on the lower area of the cargo door.

1 Apply sealant on the lower area of the cargo door:

Fig. A-FBEAA Sheet 01 and Fig. A-FBEAA Sheet 02

a Do a block of:

Corrosion Inhibiting

fillet Consistency

09-016 As required

at dimensions given in Fig. A-FBEAA Sheet 02 and make it dry out.

b Over the block already cured, apply (Refer to Fig. A-FBEAA Sheet 02):

Corrosion Inhibiting

fillet Consistency

09-016 As required

c Do the protection with:

Flexible

Polyurethane

16-021 As required

DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242

REVISION No.: 00 - May 22/12 Page: 35

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

equipment.

(2) Subtask 531242-942-002-002 - Close-up

Manpower Resources

Skills NON SPECIFIC

References

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

Task 25-54-11-400-001

Task 52-30-00-860-002

Task 53-12-14-400-001

Fig. A-FBDAB

Removal and Installation of the Fitting

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Fig. A-FBEAA

Removal and installation of the sealant

Sheet 01

Sheet 02

Fig. A-FBCAA

Installation of the fasteners

Sheet 01

Sheet 02

Sheet 03

Sheet 04

(a) Install the FWD cargo-compartment panel FIN 131CW (Refer to AMM 06-41-53,

Page Block 001 and AMM Task 25-54-11-400-001).

(b) Install the panels FIN 131AF or FIN 131PG or FIN 132GG or FIN 132MF (Refer to

AMM Task 53-12-14-400-001).

(c) Close the forward cargo-compartment door 825AR (Refer to AMM Task

52-30-00-860-002).

(d) Remove the access platform(s).

DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242

REVISION No.: 00 - May 22/12 Page: 36

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**CONF ALL

FR24

FR26 FR35 FR29

A

A

FR24A

B

N_SB_531242_5_BEAA_01_03

Figure A-FBEAA - Sheet 01

Removal and installation of the sealant

DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242

REVISION No.: 00 - May 22/12 Page: 37

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**CONF ALL

131 mm

(5.16 in)

MIN 40 mm

MIN (1.57 in) 30 mm

(1.18 in)

VIEW LOOKING FORWARD

F

W

D

01

01

02

02

01 BLOCK OF MAT. No. 09−016

02 APPLY MAT. No. 09−016 OVER THE BLOCK

NOTES:

AND PROTECT WITH MAT. No; 16.021

ALREADY CURED

B

A A

FR24

95 mm

(3.74 in)

95 mm

(3.74 in)

A A

N_SB_531242_5_BEAA_02_00

Figure A-FBEAA - Sheet 02

Removal and installation of the sealant

DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242

REVISION No.: 00 - May 22/12 Page: 38

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**CONF 001

Z130

A

FR24

FR34

B

A

C

B

N_SB_531242_5_BDAA_01_00

Figure A-FBDAA - Sheet 01

Removal and Installation of the Fitting

DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242

REVISION No.: 00 - May 22/12 Page: 39

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**CONF 001

FASTENERS TO

BE REMOVED

FASTENERS TO

BE REMOVED

F

E

D

G

H

STGR39

FR24

C

D E

J

F

W

D

FWD FWD

N_SB_531242_5_BDAA_02_01

FR24A FR24A

Figure A-FBDAA - Sheet 02

Removal and Installation of the Fitting

DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242

REVISION No.: 00 - May 22/12 Page: 40

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**CONF 001

FR24 FR24A FR25

FR24A FR24

FR24 FR24A

F

G

H

FWD

FWD

FWD

J

(40)

FITTING

L

K

NOTES:

DURING THE FASTENERS INSTALLATION APPLY MATSET No. 09−013.

AFTER THE INSTALLATION OF THE FASTENERS APPLY MATSET

No. 16−001 AND 16−018.

BETWEEN THE FITTING AND THE STRUCTURE APPLY MATSET No. 09−016.

N_SB_531242_5_BDAA_03_05

Figure A-FBDAA - Sheet 03

Removal and Installation of the Fitting

DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242

REVISION No.: 00 - May 22/12 Page: 41

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**CONF 001

FR25 FR24A

FR24A

FWD

K FWD

L

NOTES:

DURING THE FASTENERS INSTALLATION APPLY MATSET No. 09−013.

AFTER THE INSTALLATION OF THE FASTENERS APPLY MATSET

No. 16−001 AND 16−018.

BETWEEN THE FITTING AND THE STRUCTURE APPLY MATSET No. 09−016.

N_SB_531242_5_BDAA_04_04

Figure A-FBDAA - Sheet 04

Removal and Installation of the Fitting

DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242

REVISION No.: 00 - May 22/12 Page: 42

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**CONF 001

HOLE

SYMBOL ITEM OLD PN

ASNA2050DEJ4020

ASNA2026V3−7

ASNA2528−3

ITEM NEW PN DESCRIPTION REMARKS

HOLE DIAMETER

MIN MAX

5.113 mm

(0.2012 in)

5.152 mm

(0.2028 in) DIAMETER

RIVET

EN6114V3X7 BOLT

ASNA2528−3 NUT

OLD NEW

(1)(2)(3)

15

16

3

OVERSIZE

ASNA2027V3−4

ASNA2528−3

5.113 mm

(0.2012 in)

5.152 mm

(0.2028 in) DIAMETER

EN6115V3X4 BOLT

ASNA2528−3 NUT

(4)(3)

17

3

OVERSIZE

ASNA2026V3−5

ASNA2528−3

5.113 mm

(0.2012 in)

5.152 mm

(0.2028 in) DIAMETER

EN6114V3X5 BOLT

ASNA2528−3 NUT

(5)(3)

18

3

OVERSIZE

ASNA2026V4−9

ASNA2528−4 DIAMETER

EN6114V4X9 BOLT

ASNA2528−4 NUT

(6)

(30)

19

30

OVERSIZE

MS21250−04006

NSA5057−4 DIAMETER

SCREW

NUT

(7)(8)

(7)

8

NOMINAL

MS21250−04004

NSA5057−4 DIAMETER

SCREW

NUT

(9)(8)

(9)

8

NOMINAL

6.706 mm

(0.264 in)

6.747 mm

(0.2653 in)

MS21250−04006

NSA5057−4

MS21250−04004

NSA5057−4

ASNA2050DXJ4820 4.78 mm (0.188 in) 4.82 mm (0.189 in) OVERSIZE DIAMETER

ASNA2027V3−6

ASNA2528−3 DIAMETER

EN6115V3X6 BOLT

ASNA2528−3 NUT

(100)

(3)

41

3

OVERSIZE 5.113 mm

(0.2012 in)

5.152 mm

(0.2028 in)

N_SB_531242_5_BDAA_05_02

Figure A-FBDAA - Sheet 05

Removal and Installation of the Fitting

DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242

REVISION No.: 00 - May 22/12 Page: 43

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**CONF 002

Z130

A

FR24

FR34

B

A

C

B

N_SB_531242_5_BDAB_01_00

Figure A-FBDAB - Sheet 01

Removal and Installation of the Fitting

DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242

REVISION No.: 00 - May 22/12 Page: 44

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**CONF 002

FASTENERS TO

BE REMOVED

FASTENERS TO

BE REMOVED

F

E

D

G

H

STGR39

FR24

C

D E

J

F

W

D

FWD FWD

N_SB_531242_5_BDAB_02_00

Figure A-FBDAB - Sheet 02

Removal and Installation of the Fitting

DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242

REVISION No.: 00 - May 22/12 Page: 45

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**CONF 002

FR24 FR24A FR25

FR24A FR24

FR24 FR24A

F

G

H

FWD

FWD

FWD

(40)

FITTING

L

K

J

NOTES:

DURING THE FASTENERS INSTALLATION APPLY MATSET No. 09−013.

AFTER THE INSTALLATION OF THE FASTENERS APPLY MATSET

No. 16−001 AND 16−018.

BETWEEN THE FITTING AND THE STRUCTURE APPLY MATSET No. 09−016.

N_SB_531242_5_BDAB_03_03

Figure A-FBDAB - Sheet 03

Removal and Installation of the Fitting

DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242

REVISION No.: 00 - May 22/12 Page: 46

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**CONF 002

FR25 FR24A

FR24A

FWD

K FWD

L

NOTES:

DURING THE FASTENERS INSTALLATION APPLY MATSET No. 09−013.

AFTER THE INSTALLATION OF THE FASTENERS APPLY MATSET

No. 16−001 AND 16−018.

BETWEEN THE FITTING AND THE STRUCTURE APPLY MATSET No. 09−016.

N_SB_531242_5_BDAB_04_02

Figure A-FBDAB - Sheet 04

Removal and Installation of the Fitting

DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242

REVISION No.: 00 - May 22/12 Page: 47

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**CONF 002

HOLE

SYMBOL ITEM OLD PN

ASNA2050DXJ4020

ASNA2026V3−7

ASNA2528−3

ITEM NEW PN DESCRIPTION REMARKS

HOLE DIAMETER

MIN MAX

5.113 mm

(0.2012 in)

5.152 mm

(0.2028 in) DIAMETER

RIVET

EN6114V3X7 BOLT

ASNA2528−3 NUT

OLD NEW

(1)(2)(3)

15

16

3

OVERSIZE

ASNA2027V3−4

ASNA2528−3

5.113 mm

(0.2012 in)

5.152 mm

(0.2028 in) DIAMETER

EN6115V3X4 BOLT

ASNA2528−3 NUT

(4)(3)

17

3

OVERSIZE

ASNA2026V3−5

ASNA2528−3

5.113 mm

(0.2012 in)

5.152 mm

(0.2028 in) DIAMETER

EN6114V3X5 BOLT

ASNA2528−3 NUT

(5)(3)

18

3

OVERSIZE

ASNA2026V4−9

ASNA2528−4 DIAMETER

EN6114V4X9 BOLT

ASNA2528−4 NUT

(6)

(30)

19

30

OVERSIZE

MS21250−04006

NSA5057−4 DIAMETER

SCREW

NUT

(7)(8)

(7)

8

NOMINAL

MS21250−04004

NSA5057−4 DIAMETER

SCREW

NUT

(9)(8)

(9)

8

NOMINAL

6.706 mm

(0.264 in)

6.747 mm

(0.2653 in)

MS21250−04006

NSA5057−4

MS21250−04004

NSA5057−4

ASNA2050DXJ4820 4.78 mm (0.188 in) 4.82 mm (0.189 in) OVERSIZE DIAMETER

EN6114V3−7

ASNA2528−3 DIAMETER

EN6114V3X7 BOLT

ASNA2528−3 NUT

(14)

(3)

16

3

OVERSIZE 5.113 mm

(0.2012 in)

5.152 mm

(0.2028 in)

ASNA2528−3 DIAMETER

EN6115V3X6 BOLT

ASNA2528−3 NUT

(100)

(3)

41

3

OVERSIZE 5.113 mm

(0.2012 in)

5.152 mm

(0.2028 in)

ASNA2027V3−6

N_SB_531242_5_BDAB_05_02

Figure A-FBDAB - Sheet 05

Removal and Installation of the Fitting

DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242

REVISION No.: 00 - May 22/12 Page: 48

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**CONF ALL

N_SB_531242_5_BAAA_01_00

Z130

A

FR24

FR34

B

A

C

B

Figure A-FBAAA - Sheet 01

Inspection of the surrounding holes and area to be inspected

DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242

REVISION No.: 00 - May 22/12 Page: 49

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**CONF ALL

FR24

STGR39

FR24

STGR39

HOLES TO BE

INSPECTED

E

F

D

STGR39

FR24

D E

F

W

D C

N_SB_531242_5_BAAA_02_02

Figure A-FBAAA - Sheet 02

Inspection of the surrounding holes and area to be inspected

DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242

REVISION No.: 00 - May 22/12 Page: 50

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**CONF ALL

STGR39 STGR38

HOLE

SYMBOL ITEM

HOLE DIAMETER

MIN MAX

4.06 mm

(0.160 in)

4.17 mm

(0.164 in)

4.125 mm

(0.162 in)

4.160 mm

(0.1637 in)

FR24

STGR40

HOLES TO BE INSPECTED

(10)

(11)

(12)

F

F

W

D

EXISTING NOMINAL

DIAMETER

DESCRIPTION REMARKS

RIVET

PIN COLLAR EXISTING NOMINAL

DIAMETER

4.125 mm

(0.162 in)

4.160 mm

(0.1637 in)

(50)

(12)

PIN COLLAR EXISTING NOMINAL

DIAMETER

MISSING HOLE POSITION

N_SB_531242_5_BAAA_03_02

Figure A-FBAAA - Sheet 03

Inspection of the surrounding holes and area to be inspected

DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242

REVISION No.: 00 - May 22/12 Page: 51

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**CONF 001

QUESTION

ACTION

FINDING

REMOVE THE 5 SURROUNDING FASTENERS

NO OF THE REMOVED FASTENERS YES

AS PER NTM 51−10−01 PART 6 PROCEDURE A

OF THE 5 HOLES

DO A ROTOTEST INSPECTION

CONTACT AIRBUS AND

APPLY CORRECTIVE ACTION 

YES CRACKS FINDING NO

OVERSIZE THE 5 HOLES

AND INSTALL NEW FASTENERS

INSTALL THE MISSING FASTENER

DRILL THE MISSING HOLE AND

REFER TO APPENDIX 01

NO FURTHER ACTION

SEND TO AIRBUS THE

INSPECTION REPORT

HOLES

AT NOMINAL DIAMETER

DO A DETAILED INSPECTION AT NOSE FORWARD FUSELAGE AT FR24

STRG39 (RH SIDE) FOR MISSING FASTENER AND DRILLING AT THE

THRESHOLD GIVEN IN THE PLANNING INFORMATION PARAGRAPH E.(2)

REFER TO SUBTASK 531242−020−002−001

REFER TO SUBTASK 531242−420−003−001

DEFINED BY AIRBUS

BEFORE NEXT FLIGHT

MISSING YES FASTENER NO

REFER TO SUBTASK 531242−220−001−001

N_SB_531242_5_FAAA_01_01

Figure A-FFAAA - Sheet 01

Flow Chart

DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242

REVISION No.: 00 - May 22/12 Page: 52

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**CONF 002

QUESTION

ACTION

FINDING

REMOVE THE 5 SURROUNDING FASTENERS

NO OF THE REMOVED FASTENERS YES

AS PER NTM 51−10−01 PART 6 PROCEDURE A

OF THE 5 HOLES

DO A ROTOTEST INSPECTION

CONTACT AIRBUS AND

APPLY CORRECTIVE ACTION 

YES CRACKS FINDING NO

OVERSIZE THE 5 HOLES

AND INSTALL NEW FASTENERS

INSTALL THE MISSING FASTENER

DRILL THE MISSING HOLE AND

REFER TO APPENDIX 01

NO FURTHER ACTION

SEND TO AIRBUS THE

INSPECTION REPORT

HOLES

AT NOMINAL DIAMETER

DO A DETAILED INSPECTION AT NOSE FORWARD FUSELAGE AT FR24

STRG39 (RH SIDE) FOR MISSING FASTENER AND DRILLING AT THE

THRESHOLD GIVEN IN THE PLANNING INFORMATION PARAGRAPH E.(2)

REFER TO SUBTASK 531242−020−002−001

REFER TO SUBTASK 531242−420−003−002

DEFINED BY AIRBUS

BEFORE NEXT FLIGHT

MISSING YES FASTENER NO

REFER TO SUBTASK 531242−220−001−003

N_SB_531242_5_FAAB_01_00

Figure A-FFAAB - Sheet 01

Flow Chart

DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242

REVISION No.: 00 - May 22/12 Page: 53

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**CONF ALL

Z130

A

FR24

FR34

B

A

C

B

N_SB_531242_5_BCAA_01_00

Figure A-FBCAA - Sheet 01

Installation of the fasteners

DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242

REVISION No.: 00 - May 22/12 Page: 54

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**CONF ALL

FR24

STGR39

FR24

STGR39

E

F

D

STGR39

FR24

D E

N_SB_531242_5_BCAA_02_01

F

W

D C

Figure A-FBCAA - Sheet 02

Installation of the fasteners

DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242

REVISION No.: 00 - May 22/12 Page: 55

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**CONF ALL

HOLE

SYMBOL ITEM PN DESCRIPTION

HOLE DIAMETER

MIN MAX

4.85 mm

(0.191 in)

4.95 mm

(0.195 in) ASNA2049DXJ4820 RIVET

STGR39 STGR38

FR24

STGR40

EN6114V3−7 BOLT

ASNA2528−3 NUT

4.78 mm

(0.188 in)

4.82 mm

(0.190 in)

13

14

3

F

F

W

D

NEXT NOMINAL

DIAMETER

NOMINAL

DIAMETER

REMARKS

(40)

FITTING

EN6114V3X3 BOLT

ASNA2528−3 NUT

5.113 mm

(0.2012 in)

5.152 mm

(0.2028 in)

60

3

NEXT NOMINAL

DIAMETER

A

A

NOTES:

DURING THE FASTENERS INSTALLATION

AFTER THE INSTALLATION OF THE FASTENERS

APPLY MATSET No. 16−001 AND 16−018.

HOLE TO BE

APPLY MATSET No. 09−013.

FR24 FR24A

RIVETS UNDER THE FITTING

A A

EN6114V3X4 BOLT

ASNA2528−3 NUT

5.113 mm

(0.2012 in)

5.152 mm

(0.2028 in)

70

3

NEXT NOMINAL

DIAMETER

DRILLED

N_SB_531242_5_BCAA_03_07

Figure A-FBCAA - Sheet 03

Installation of the fasteners

DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242

REVISION No.: 00 - May 22/12 Page: 56

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SERVICE BULLETIN

**CONF ALL

FR24

MISSING FASTENER

VIEW FROM

THE OUTSIDE OF

THE AIRCRAFT

NOTE:

DRILL FROM THE OUTSIDE OF THE AIRCRAFT.

N_SB_531242_5_BCAA_04_00

DRILL THE MISSING HOLE TO THE SAME DISTANCE FROM THE SURROUDING HOLE.

FWD

Figure A-FBCAA - Sheet 04

Installation of the fasteners

DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242

REVISION No.: 00 - May 22/12 Page: 57

5

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SERVICE BULLETIN

This Page Intentionally Left Blank

DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242

REVISION No.: 00 - May 22/12 Page: 58

5

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SERVICE BULLETIN

Appendix 01 - Inspection Report

**CONF ALL

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

forwarded to AIRBUS department SEES4, on the attached inspection report sheet.

DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242

REVISION No.: 00 - May 22/12 Page: 1

5

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SERVICE BULLETIN

Appendix 01 - Inspection Report

**CONF ALL

HOLE H1

HOLE H2

HOLE H3

HOLE H4

NO CRACK CRACK

LENGTH

mm

HOLE H5

INSPECTION REPORT

SERVICE BULLETIN No. :

A/C MSN :

FLIGHT CYCLES :

FLIGHT HOURS :

A320−53A1242

DATE OF INSPECTION :

RETURN TO :

AIRBUS

CUSTOMER SERVICES ENGINEERING − SEES4

PAX DOORS − FUSELAGE (SA/LA) − WINDOWS −

INSPECTION METHOD :

CENTER WING BOX (SA/LA)

ROTATING PROBE

TESTING

1 ROND POINT MAURICE BELLONTE

31707 BLAGNAC CEDEX

FRANCE

FAX +33 (0)5 61 93 36 14

in

Structure.sbinspectionresult@airbus.com

FASTENER MISSING YES NO

N_SB_531242_5_RAAA_01_01

Figure A-FRAAA - Sheet 01

Inspection Report

DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242

REVISION No.: 00 - May 22/12 Page: 2

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SERVICE BULLETIN

Appendix 01 - Inspection Report

**CONF ALL

STGR39 STGR38

FR24

STGR40

SURROUNDING HOLES TO BE INSPECTED

F

F

W

D

H2

H1 H5

H4

H3

CHECK FOR MISSING FASTENER

N_SB_531242_5_RAAA_02_01

Figure A-FRAAA - Sheet 02

Inspection Report

DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242

REVISION No.: 00 - May 22/12 Page: 3

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SERVICE BULLETIN

REPORTING SHEET

TITLE: FUSELAGE - NOSE FORWARD FUSELAGE - INSPECTION OF MISSING

FASTENER AND DRILLING AT FR 24 STRG 39 RH SIDE.

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 22/12 SERVICE BULLETIN No.: A320-53-1242

REVISION No.: 00 - May 22/12 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: May 22/12 SERVICE BULLETIN No.: A320-53-1242

REVISION No.: 00 - May 22/12 Page: 1

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