@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 - ONE MISSING FASTENER

AT FR24 STRG 25 AND 26 RH SIDE

**CONF ALL

MODIFICATIONS

None

REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

One fastener, at FR24 between STRG 25/26 RH side was discovered missing in production.

This missing fastener, a 4 mm diameter aluminium rivet (ASNA2050DXJ040), normally connects

together FR24 and FR24 Tee.

This Service Bulletin calls for a Rototest inspection of the two adjacent fastener holes and some

corrective actions if crack is found or not.

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.

MATERIAL PRICE INFORMATION

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Component COMPA01 1 See SB Rivet

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SERVICE BULLETIN

SUMMARY

EFFECTIVITY

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

89X AAW ABY AFL AFR AVA AXM BAW BER CBJ CCA CEB CES

CHH CQH CSC CSN CSZ DKH DLH GAP GLG GOW IGO ISR JSA

JST LAA LAN NKS PIC QTR SLK SVA TAM TGW UZB VRD

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

MANPOWER

Task 531247-832-801-001: Inspection

TOTAL MANHOURS 5.50

ELAPSED TIME (HOURS) 5.50

APPENDICES

Appendix 01 : Inspection Report

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SUMMARY

**CONF ALL

N_SB_531247_5_SAAA_01_00

STGR20RH

A

C

B

FR24

FR24

STGR26RH

A

Y−607

Figure A-FSAAA - Sheet 01

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SUMMARY

**CONF ALL

HOLES TO BE INSPECTED

HOLES TO BE INSPECTED

C

B MISSING HOLE

AND FASTENER MISSING HOLE

AND FASTENER

NOTE:

01 VIEW SHOWN AFTER THE REMOVAL OF

THE NECESSARY INSULATION BLANKETS

01

01 FR24

FR24

VIEW LOOKING AFT N_SB_531247_5_SAAA_02_02

Figure A-FSAAA - Sheet 02

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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 - ONE MISSING FASTENER

AT FR24 STRG 25 AND 26 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

320-214 320-216 320-232 320-233 321-211 321-213 321-231

(2) Effectivity by MSN

4338 4371 4374-4375 4377 4381-4384 4386-4388 4390-4402 4404-4409 4411-4417

4419-4421 4423-4424 4426 4429-4436 4438-4443 4445-4450 4453-4454 4456-4469

4471-4472 4474-4481 4483-4498 4500 4504-4506 4509

(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

89X 4411

AAW 4489

ABY 4468

AFL 4453 4461 4498 4500

AFR 4402

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OPERATOR MSN

AVA 4381

AXM 4386 4390 4404 4426 4458 4462 4477 4486

BAW 4464

BER 4433 4463 4478

CBJ 4388

CCA 4377 4472 4494

CEB 4447

CES 4374 4423

CHH 4412 4440 4471 4483 4505

CQH 4375

CSC 4420 4424

CSN 4338 4387 4396 4416 4430 4456

CSZ 4407 4409 4435 4474

DKH 4401 4429

DLH 4398 4449

GAP 4415 4475 4504

GLG 4487

GOW 4399 4438

IGO 4384 4481 4488 4506

ISR 4413

JSA 4443

JST 4434 4460 4466 4495 4497

LAA 4405 4450 4490

LAN 4383 4400 4439 4476 4509

NKS 4431

PIC 4459

QTR 4382 4406 4436 4479 4496

SLK 4457

SVA 4391 4392 4393 4394 4397 4408 4414 4419 4432 4442 4454 4467

4484

TAM 4441 4446 4465

TGW 4421 4445 4469 4491 4493

UZB 4371 4395 4417 4485 4492

VRD 4448 4480

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(4) Configuration by MSN

MSN CONFIGURATION

4338 4371 4374 4375 4377 4381 4382 4383 4384 4386 4387

4388 4390 4391 4392 4393 4394 4395 4396 4397 4398 4399

4400 4401 4402 4404 4405 4406 4407 4408 4409 4411 4412

4413 4414 4415 4416 4417 4419 4420 4421 4423 4424 4426

4429 4430 4431 4432 4433 4434 4435 4436 4438 4439 4440

4441 4442 4443 4445 4446 4447 4448 4449 4450 4453 4454

4456 4457 4458 4459 4460 4461 4462 4463 4464 4465 4466

4467 4468 4469 4471 4472 4474 4475 4476 4477 4478 4479

4480 4481 4483 4484 4485 4486 4487 4488 4489 4490 4491

4492 4493 4494 4495 4496 4497 4498 4500 4504 4505 4506

4509

001

(5) Configuration definition

**CONF 001

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

standard configuration.

(6) Material Effectivity

MATERIAL QTY PER A/C SEE NOTES

Component COMPA01 1

Consumable CMLA01 1

B. CONCURRENT REQUIREMENTS

None

C. REASON

(1) History

One fastener, at FR24 between STRG 25/26 RH side was discovered missing in

production.

This missing fastener, a 4 mm diameter aluminium rivet (ASNA2050DXJ040), normally

connects together FR24 and FR24 Tee.

(2) Objective/Action

This Service Bulletin calls for a Rototest inspection of the two adjacent fastener holes

and some corrective actions if crack is found or not.

(3) Advantages

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

the aircraft.

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(4) Operational/Maintenance Consequences

D. DESCRIPTION

To accomplish this Service Bulletin it is necessary to :

Task 531247-832-801-001: Inspection

(1) Remove the two Fasteners to be Inspected at FR 24 between STRG 25 and 26 RH

(2) Special Detailed Inspection of the two Holes at FR 24 between STRG 25 and 26 RH

side

(3) Modify the Frame 24 attachment between STRG 25 and 26 RH side

E. COMPLIANCE

(1) Classification

RECOMMENDED: Service Bulletin recommended to be accomplished to prevent

significant operational disruptions.

(2) Accomplishment Timescale

Accomplishment of this Service Bulletin is recommended at the earliest opportunity

where manpower and facilities are available.

The inspection described in this Service Bulletin must be done at next convenient

opportunity no later than 24000 Flight Cycle from entry into service.

F. APPROVAL

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

Organisation Approval No. EASA.21J.031.

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

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

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

before incorporation of the Service Bulletin.

G. MANPOWER

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

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

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

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

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

included.

Task 531247-832-801-001: Inspection

Get Access 0.50

On Aircraft

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Task 531247-832-801-001: Inspection

Remove the two Fasteners to be Inspected at FR 24

between STRG 25 and 26 RH

0.50

Special Detailed Inspection of the two Holes at FR 24

between STRG 25 and 26 RH side

1.50

Modify the Frame 24 attachment between STRG 25

and 26 RH side

2.50

Close-Up 0.50

TOTAL MANHOURS 5.50

ELAPSED TIME (HOURS) 5.50

H. WEIGHT AND BALANCE

Not Changed

I. ELECTRICAL LOAD DATA

Not Changed

J. REFERENCES

Aircraft Maintenance Manual (AMM) 06-41-53 12-34-24 25-54-11

25-80-00 52-30-00

Consumable Material List (CML)

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

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

Standards Manual (SM)

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

51-43-00 51-44-00 51-47-00

K. PUBLICATION AFFECTED

None

L. INTERCHANGEABILITY/MIXABILITY

Not Applicable

M. SPARES

None

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2. MATERIAL INFORMATION

**CONF ALL

A. MATERIAL - PRICE AND AVAILABILITY

(1) Procurement Addresses

Component COMPA01 Airbus Material, Logistics and Suppliers do

not stock standard hardware as competetive

multiple suppliers ensure access to minimum

prices Airbus recommends customers with

aircraft shown in the effectivity of this Service

Bulletin to send a purchase order to B/E

Aerospace. The address is :

B/E AEROSPACE INC

CONSUMABLES MANAGEMENT

10000 NW 15TH Terrace Miami

FL 33172

USA

Tel EMEA : +49 (0) 40 822 285 31500

Tel US : +1 305 925 2600

Tel ASIA : +1 310 900 1300

Fax EMEA : +49 (0) 40 822 285 31010

Fax US : +1 305 507 7191

Fax ASIA : +1 310 819 1200

SITA : MIAMMCR

E-Mail : AOGdesk_CMG@beaerospace.com

web address : www.beconsumables.com

or, alternatively any other source on the open

market.

(2) Price and Availability

No Airbus kit will be provided.

Operator supplied standard hardware parts required to accomplish this Service Bulletin

are to be supplied from the Operator’s stock.

B. INDUSTRY SUPPORT INFORMATION

For the accomplishment of this Service Bulletin before Mar 01/2014, AIRBUS will credit the

manhours indicated in this Service Bulletin at the agreed in-house warranty labor rate for

claims received not later than 90 days after completion of the last affected aircraft of your

fleet.

C. LIST OF COMPONENTS

No Kit

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D. LIST OF MATERIALS - OPERATOR SUPPLIED

(1) Consumable Materials

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO CML

MAT. No.

QTY PER A/C SEE

NOTES

Corrosion Inhibiting fillet

Consistency

09-016 As required

Solvent General Purpose 11-026 As required

(2) Components

Component COMPA01

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

NOTES

1 ASNA2050DXJ4828 2 RIVET

2 ASNA2050DXJ4020 1 RIVET

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.

(3) Equipment

None

E. PARTS TO BE RE-IDENTIFIED BY OPERATOR

None

F. TOOLING

(1) Tooling - Price and Availability

Refer to NTM 51-10-01

(2) Tools

None

(3) Special Tools

None

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3. ACCOMPLISHMENT INSTRUCTIONS

Task 531247-832-801-001 - 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

Zone

825

Manpower

TOTAL MANHOURS 5.50

ELAPSED TIME (HOURS) 5.50

A. GENERAL

(1) Subtask 531247-910-001-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Solvent General Purpose 11-026 As required

References

Consumable Material List (CML)

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References

Structural Repair Manual (SRM) 51-23-11

51-23-12

51-42-11

51-43-00

51-44-00

51-47-00

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

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

Solvent General

Purpose

11-026 As required

(c) For the paint coating (Refer to SRM 51-23-11).

(d) For the special protection (Refer to SRM 51-23-12).

(e) For fastener spacing and margin data (Refer to SRM 51-47-00).

(f) For alternative and substitute fasteners, refer to SRM 51-43-00.

(g) Remove/install the fasteners, (Refer to SRM 51-42-11).

(h) For fasteners hole diameters and drill and deburr data (Refer to SRM 51-44-00).

(i) Cut the rivets to the necessary length.

(2) Subtask 531247-839-001-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

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

Service Bulletin.

B. PREPARATION

(1) Subtask 531247-941-001-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

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

Task 12-34-24-869-002

Task 25-54-11-000-001

Task 25-80-00-000-001

Task 52-30-00-860-001

Task 52-30-00-860-003

Task 52-30-00-860-005

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

12-34-24-869-002).

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

(c) Open the FWD cargo/compartment door 825AR (Refer to AMM

Task 52-30-00-860-001 or AMM Task 52-30-00-860-003 or AMM Task

52-30-00-860-005).

(d) Remove the partition panel 132EW at the Frame 24 (Refer to AMM 06-41-53, Page

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

(e) Remove the necessary insulation blankets (Refer to AMM Task 25-80-00-000-001).

C. PROCEDURE

(1) Subtask 531247-020-001-001 - Remove the two Fasteners to be Inspected at FR 24

between STRG 25 and 26 RH

Work Zones and Access Panels

Zone Access/Work location

825

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

References

Fig. A-FBCAA

Modification of the Frame 24 between

STR 25 and 26 RH.

Sheet 01

(a) Remove the two fasteners Item (1) to be inspected at Frame 24 :

refer to Fig. A-FBCAA Sheet 01

2 Rivet Item (1) Discard

(2) Subtask 531247-280-001-001 - Special Detailed Inspection of the two Holes at FR

24 between STRG 25 and 26 RH side

Work Zones and Access Panels

Zone Access/Work location

825

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Manpower Resources

Manhours 1.50

Minimum number of person 1

Subtask elapsed time 1.50

Skills NON DESTRUCTIVE

TESTING

References

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

Fig. A-FBAAA

Inspection Area

Sheet 01

Sheet 02

Fig. A-FFAAA

Flow Chart

Sheet 01

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

02.

(b) At Frame 24, between STRG 25 and 26 RH side, do a special detailed inspection

(Rototest inspection) of the two adjacent holes (Refer to NTM 51-10-01).

refer to Fig. A-FFAAA Sheet 01.

- If crack is found, contact Airbus and apply the corrective action defined by

Airbus before next flight.

- If no crack is found, modify the Frame 24 between STRG 25 and 26 RH as

described in SUBTASK 531247-833-001-001.

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

(3) Subtask 531247-833-001-001 - Modify the Frame 24 attachment between STRG 25

and 26 RH side

Manpower Resources

Manhours 2.50

Minimum number of person 1

Subtask elapsed time 2.50

Skills AIRFRAME

Material necessary to do the job

Component COMPA01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 ASNA2050DXJ4828 2 RIVET

2 ASNA2050DXJ4020 1 RIVET

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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

References

Fig. A-FBCAA

Modification of the Frame 24 between

STR 25 and 26 RH.

Sheet 01

(a) Modify the Frame 24, between STR 25 and 26 RH:

refer to Fig. A-FBCAA

1 Oversize the two inspected holes to a diameter comprised between 4.85 mm

(0.191 in.) and 4.95 mm (0.195 in.) as shown on Fig. A-FBCAA Sheet 01.

2 Install :

refer to Fig. A-FBCAA Sheet 01

2 Rivet ASNA2050DXJ4828 Item 1

3 Drill one new hole between the two inspected holes to a diameter comprised

between 4.06 mm (0.160 in.) and 4.17 mm (0.164 in.) as shown on Fig. AFBCAA Sheet 01.

NOTE: Respect the alignment, the space margin between the holes

and the edge margin in the tee.

4 Install :

refer to Fig. A-FBCAA Sheet 01

1 Rivet ASNA2050DXJ4020 Item 2

NOTE: Wet install with sealant :

Corrosion Inhibiting

fillet Consistency

09-016 As required

D. TEST

None

E. CLOSE-UP

(1) Subtask 531247-942-001-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

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References

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

Task 25-54-11-400-001

Task 25-80-00-400-001

Task 52-30-00-860-002

Task 52-30-00-860-004

Task 52-30-00-860-009

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

equipment

(b) Install the insulation blankets removed for access (Refer to AMM Task

25-80-00-400-001).

(c) Install the partition panel 132EWremoved for access (Refer to AMM 06-41-53, Page

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

(d) Close the FWD cargo/compartment door 825AR (Refer to AMM

Task 52-30-00-860-002 or AMM Task 52-30-00-860-004 or AMM Task

52-30-00-860-009).

(e) Remove the access platform(s).

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

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**CONF ALL

STGR20RH

A

C

B

FR24

FR24

STGR26RH

A

Y−607

N_SB_531247_5_BAAA_01_00

Figure A-FBAAA - Sheet 01

Inspection Area

DATE: Jul 15/11 SERVICE BULLETIN No.: A320-53-1247

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**CONF ALL

HOLES TO BE INSPECTED

HOLES TO BE INSPECTED

C

B MISSING HOLE

AND FASTENER MISSING HOLE

AND FASTENER

NOTE:

01 VIEW SHOWN AFTER THE REMOVAL OF

THE NECESSARY INSULATION BLANKETS

01

01 FR24

FR24

VIEW LOOKING AFT N_SB_531247_5_BAAA_02_02

Figure A-FBAAA - Sheet 02

Inspection Area

DATE: Jul 15/11 SERVICE BULLETIN No.: A320-53-1247

REVISION No.: 00 - Jul 15/11 Page: 16

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**CONF ALL

QUESTION

ACTION

FINDING

AT THE THRESHOLD GIVEN IN THE PLANNING

INFORMATION PARAGRAPH E.(2).

YES CRACK NO

(REFER TO THE NTM 51−10−01) OF THE TWO ADJACENT

HOLES AT FR24, BETWEEN STGR25 AND 26RH SIDE

DRILL THE MISSING HOLE AND INSTALL

RIVETS AS DESCRIBED IN

OVERSIZE THE TWO ADJACENT HOLES,

SUBTASK 531247−833−001−001

NO FURTHER ACTION

CONTACT AIRBUS

AND APPLY THE CORRECTIVE

ACTION DEFINED BY AIRBUS

BEFORE NEXT FLIGHT

DO A SPECIAL DETAILED INSPECTION (ROTOTEST INSPECTION) 

N_SB_531247_5_FAAA_01_02

Figure A-FFAAA - Sheet 01

Flow Chart

DATE: Jul 15/11 SERVICE BULLETIN No.: A320-53-1247

REVISION No.: 00 - Jul 15/11 Page: 17

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**CONF ALL

STGR20RH

A

FR24

STGR26RH

Y−607

FR24

B

A STGR25

STGR26

NOTE:

01 RESPECT THE ALIGNMENT, THE SPACE MARGIN BETWEEN THE HOLES

HOLE

SYMBOL ITEM PN DESCRIPTION REMARKS

HOLE DIAMETER

MIN MAX

4.06 mm

(0.160 in)

4.17 mm

(0.164 in)

4.85 mm

(0.191 in)

4.95 mm

(0.195 in)

ASNA2050DXJ4020 RIVET

VIEW LOOKING FORWARD

ASNA2050DXJ4828 RIVET

OLD

ITEM

NEW

01

2

(1) 1

N

N

B

FASTENERS NOT AFFECTED

N HEAD ON VISIBLE SIDE

FR24

AND THE EDGE MARGIN IN THE TEE.

02 WET INSTALL WITH SEALANT MAT. No. 09−016.

02

N_SB_531247_5_BCAA_01_03

Figure A-FBCAA - Sheet 01

Modification of the Frame 24 between STR 25 and 26 RH.

DATE: Jul 15/11 SERVICE BULLETIN No.: A320-53-1247

REVISION No.: 00 - Jul 15/11 Page: 18

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Appendix 01 : Inspection Report

**CONF ALL

The result of the inspection, including no findings, replacement or actions to be done, must be

forwarded to Airbus Department SEES4, on the attached inspection report sheet.

DATE: Jul 15/11 SERVICE BULLETIN No.: A320-53-1247

REVISION No.: 00 - Jul 15/11 Page: 1

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SERVICE BULLETIN

Appendix 01 : Inspection Report

**CONF ALL

INSPECTION REPORT

SERVICE BULLETIN No. :

A/C MSN :

FLIGHT CYCLES :

FLIGHT HOURS :

A320−53−1247

DATE OF INSPECTION :

RETURN TO :

AIRBUS

CUSTOMER SERVICES ENGINEERING − SEES4

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

INSPECTION METHOD :

CENTER WING BOX (SA/LA)

1 ROND POINT MAURICE BELLONTE

31707 BLAGNAC CEDEX

FRANCE

FAX +33 (0)5 61 93 36 14

ADJACENT HOLES

(ROTOTEST INSPECTION)

N_SB_531247_5_RAAA_01_01

CRACK IN THE TWO

HOLE(S)

AFFECTED

OF THE CRACK

ORIENTATION

LAYER

AFFECTED

OF THE CRACK

DIMENSION

Figure A-FRAAA - Sheet 01

Inspection Report

DATE: Jul 15/11 SERVICE BULLETIN No.: A320-53-1247

REVISION No.: 00 - Jul 15/11 Page: 2

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REPORTING SHEET

TITLE: FUSELAGE - NOSE FORWARD FUSELAGE - ONE MISSING FASTENER

AT FR24 STRG 25 AND 26 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: Jul 15/11 SERVICE BULLETIN No.: A320-53-1247

REVISION No.: 00 - Jul 15/11 Page: 1

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QUALITY PERCEPTION FORM

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

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

improve the quality of our Service Bulletins.

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

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

- Quality rating of this SB 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: Jul 15/11 SERVICE BULLETIN No.: A320-53-1247

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