@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: 57

TITLE: WINGS - OUTER WING - REFUEL APERTURE - INSPECTION OF

ELECTRICAL BONDING

**CONF ALL

MODIFICATIONS

None

REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

Cases of corrosion findings have been experienced on the overwing refuelling aperture (used for gravity

filling the fuel tank) on the wing top skin. The reported corrosion was on the mating surface of the

aperture flange, underneath the refuel adaptor. Corrosion findings have been repaired on a case by

case basis.

On the aircraft in the effectivity of this Service Bulletin, Repair Instruction R572 58539 Iss A incorrectly

gave requirements to apply primer coating on the mating surface. This primer coating can prevent

proper electrical bonding provision between the overwing refuel cap adaptor and the wing skin.

Electrical bonding is performed to prevent the accumulation of electrostatic charges and provide a path

for conveying lightning strike. In this case, electrical bonding should be achieved between the bare

metal surfaces of the refuel adaptor and the top skin panel.

NOTE: To ensure conservative coverage at aircraft level, this inspection is to be accomplished

on both wings, regardless of whether repairs were only performed on one wing.

This Service Bulletin details instructions to carry out an electrical bonding check to verify the bond

between the refuel adaptor and the top skin panel. If the bonding check fails, the refuel adaptor is

removed and the surface treatment on the aperture flange is removed. If corrosion is apparent, a repair

instruction is referenced. A conversion coating and a thin layer of sealant is applied (electrical bonding

is achievable through these mediums) and the refuel adaptor is re-installed. A further electrical bonding

check is then carried out.

Accomplishment of this Service Bulletin will make sure that there is electrical bonding between the

overwing refuel adaptor and the top skin panel.

GENERAL EVALUATION

EVALUATION TABLE

COMPLIANCE RECOMMENDED (1) CANCELS INSPECTION SB NO

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SUMMARY

EVALUATION TABLE

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

No Material

EFFECTIVITY

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

AAF ACA AFR AIJ AUA BAW BEL BGH BMA CCA CYP DAL DLH

FHY GWY ISS IWD JET KKK LBT SSV SVR SWR TAM TCX TRK

UAL USA VLK

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 571152-832-895-001: Inspection

TOTAL MANHOURS 12.50

ELAPSED TIME (HOURS) 7.0

APPENDICES

None

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SUMMARY

**CONF ALL

RIB19

RIB20

540PB

(640PB)

A

CAP

LANYARD

O−RING

AFFECTED AREA

ADAPTOR

WING SKIN PANEL No. 2

A

44QM

(45QM)

42QM

(43QM)

N_SB_571152_7_SUAA_01_01

Figure A-USUAA - Sheet 01

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SUMMARY

This Page Intentionally Left Blank

DATE: Jun 14/10 SERVICE BULLETIN No.: A320-57-1152

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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: 57

TITLE: WINGS - OUTER WING - REFUEL APERTURE - INSPECTION OF

ELECTRICAL BONDING

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

319-111 319-112 319-132 320-111 320-211 320-212 320-214 320-232

321-111 321-211 321-212 321-231

(2) Effectivity by MSN

0005 0007 0016 0039 0078 0109 0118 0120 0153 0174 0187 0203 0215 0218

0226-0228 0236-0237 0269-0270 0278 0285-0288 0294 0301 0337 0377 0462-0465

0520 0523 0528 0544 0876 0888 0921 0935 0974 1014 1102 1130 1160 1162 1177

1215 1250 1287 1336 1388 1404 1444 1449 1476 1505 1524 1564 1605 1616 1622

1640 1645 1658 1677 1691 1729 1905

(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

AAF 0888

ACA 0174

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OPERATOR MSN

AFR 0005 0007 0016 0187 0226 0227 0228 0236 0237 0270 0278 0285

0286 0287 0337 0377 0544 1404 1444 1449 1476 1505 1524 1616

1622 1640 1645 1658 1677 1691

AIJ 1162

AUA 0935

BAW 0039 0109 0120

BEL 1160 1336 1388

BGH 0294

BMA 1014 1177

CCA 0876 0921

CYP 1729

DAL 0118 0153

DLH 0078 0218 0269

FHY 0288

GWY 1564

ISS 1102

IWD 1130

JET 0215

KKK 0974

LBT 0301

SSV 1605

SVR 0203

SWR 0520

TAM 1215

TCX 1250

TRK 1905

UAL 0462 0463 0464 0465 0523

USA 1287

VLK 0528

(4) Configuration by MSN

MSN CONFIGURATION

0005 0007 0016 0039 0078 0109 0118 0120 0153 0174 0187

0203 0215 0218 0226 0227 0228 0236 0237 0269 0270 0278

0285 0286 0287 0288 0294 0301 0337 0377 0462 0463 0464

0465 0520 0523 0528 0544 0876 0888 0921 0935 0974 1014

1102 1130 1160 1162 1177 1215 1250 1287 1336 1388 1404

1444 1449 1476 1505 1524 1564 1605 1616 1622 1640 1645

1658 1677 1691 1729 1905

001

(5) Configuration definition

**CONF 001

Config. 01 is valid for all the aircraft given in the effectivity of this Service Bulletin as a

standard configuration.

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(6) Material Effectivity

MATERIAL QTY PER A/C SEE NOTES

Consumable CMLB01 As required

B. CONCURRENT REQUIREMENTS

None

C. REASON

(1) History

Cases of corrosion findings have been experienced on the overwing refuelling aperture

(used for gravity filling the fuel tank) on the wing top skin. The reported corrosion was on

the mating surface of the aperture flange, underneath the refuel adaptor. Corrosion

findings have been repaired on a case by case basis.

On the aircraft in the effectivity of this Service Bulletin, Repair Instruction R572 58539

Iss A incorrectly gave requirements to apply primer coating on the mating surface. This

primer coating can prevent proper electrical bonding provision between the overwing

refuel cap adaptor and the wing skin.

Electrical bonding is performed to prevent the accumulation of electrostatic charges and

provide a path for conveying lightning strike. In this case, electrical bonding should be

achieved between the bare metal surfaces of the refuel adaptor and the top skin panel.

NOTE: To ensure conservative coverage at aircraft level, this inspection is to be

accomplished on both wings, regardless of whether repairs were only

performed on one wing.

(2) Objective/Action

This Service Bulletin details instructions to carry out an electrical bonding check to verify

the bond between the refuel adaptor and the top skin panel. If the bonding check fails,

the refuel adaptor is removed and the surface treatment on the aperture flange is

removed. If corrosion is apparent, a repair instruction is referenced. A conversion coating

and a thin layer of sealant is applied (electrical bonding is achievable through these

mediums) and the refuel adaptor is re-installed. A further electrical bonding check is then

carried out.

(3) Advantages

Accomplishment of this Service Bulletin will make sure that there is electrical bonding

between the overwing refuel adaptor and the top skin panel.

(4) Operational/Maintenance Consequences

None

D. DESCRIPTION

To accomplish this Service Bulletin it is necessary to :

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Task 571152-832-895-001: Inspection

(1) Inspection - Bonding Test

(2) Removal of Primer - Inspection for Corrosion

(3) Repair

E. COMPLIANCE

(1) Classification

RECOMMENDED: Service Bulletin recommended to be accomplished to prevent

significant operational disruptions.

(2) Accomplishment Timescale

Accomplishment is requested at or before 24 months from the issue date of this Service

Bulletin.

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 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 571152-832-895-001: Inspection

Get Access 0.5

On Aircraft

Inspection - Bonding Test 0.5

Removal of Primer - Inspection for Corrosion 5.0

Repair 6.0

Tests 0.0

Close-Up 0.5

DATE: Jun 14/10 SERVICE BULLETIN No.: A320-57-1152

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Task 571152-832-895-001: Inspection

TOTAL MANHOURS 12.50

ELAPSED TIME (HOURS) 7.0

NOTE: If the initial bonding test is satisfactory, the manhours for removal, inspection

and repair can be deducted from the Total Manhours and the Elapsed Time

can be reduced accordingly.

H. WEIGHT AND BALANCE

Not Changed

I. ELECTRICAL LOAD DATA

Not Changed

J. REFERENCES

Aircraft Maintenance Manual (AMM) 20-21-11 20-28-00 28-11-43

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

Structural Repair Manual (SRM) 51-21-11 51-74-00 51-75-11

51-76-12 57-21-11

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

None

(2) Price and Availability

None

B. INDUSTRY SUPPORT INFORMATION

For those aircraft with findings further to inspection as per this Service Bulletin, AIRBUS will

credit the manhours for the correction at the operator’s 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

D. LIST OF MATERIALS - OPERATOR SUPPLIED

(1) Consumable Materials

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

consumable materials listed in the AMM 28-11-43 Page Block 401.

Consumable CMLB01

ITEM DESCRIPTION REFERENCE TO CML

MAT. No.

QTY PER A/C SEE

NOTES

Solvent General Purpose 11-026 As required

Chemical Conversion Coating

Yellow Aluminum

13-002 As required

Lint-Free Cotton Cloth 19-003 As required

(2) Components

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

parts listed in the AMM 28-11-43 Page Block 401.

(3) Equipment

None

E. PARTS TO BE RE-IDENTIFIED BY OPERATOR

None

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F. TOOLING

(1) Tooling - Price and Availability

None

(2) Tools

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

tools listed in the AMM 28-11-43 Page Block 401.

(3) Special Tools

None

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3. ACCOMPLISHMENT INSTRUCTIONS

Task 571152-832-895-001 - Inspection

NOTE: The instructions that follow are applicable to the LH and the RH wings.

Task Associated Data

Zone

540 640

Modified FIN

42QM 43QM

Manpower

TOTAL MANHOURS 12.50

ELAPSED TIME (HOURS) 7.0

A. GENERAL

WARNING: MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND 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, REFER TO ESPM

20-55-00, CLEANING.

(1) Subtask 571152-910-401-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 20-21-11, Page Block 201

20-28-00, Page Block 201

20-28-00, Page Block 501

Structural Repair Manual (SRM) 51-21-11

51-74-00

51-75-11

51-76-12

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References

(a) Tightening Torques for Standard Threaded Fasteners (Refer to AMM 20-21-11,

Page Block 201).

(b) Electrical Bonding - Maintenance Practice (Refer to AMM 20-28-00, Page Block

201).

(c) Electrical Bonding - Testing (Refer to AMM 20-28-00, Page Block 501).

(d) Application of Protective Treatment to Metal Parts (Refer to SRM 51-21-11).

(e) Repair of Corroded Areas (Refer to SRM 51-74-00).

(f) Paint Stripping/Removal (Refer to SRM 51-75-11).

(g) Repair of Fuel Tank Sealing (Refer to SRM 51-76-12).

(2) Subtask 571152-839-401-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

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

Service Bulletin.

B. PREPARATION

(1) Subtask 571152-941-401-001 - Job Set-up

Work Zones and Access Panels

Zone Access/Work location

540 Work location from Rib 19 to Rib 20

640 Work location from Rib 19 to Rib 20

Manpower Resources

Skills NON SPECIFIC

(a) Put access platforms in position at Zone 540 and Zone 640 between Rib 19 and

Rib 20.

C. PROCEDURE

(1) Subtask 571152-832-402-001 - Inspection - Bonding Test

Work Zones and Access Panels

Zone Access/Work location

540 Work location FIN 44-QM

640 Work location FIN 45-QM

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Manpower Resources

Manhours 0.5

Minimum number of person 2

Subtask elapsed time 0.5

Skills ELECTRICAL

References

Aircraft Maintenance Manual (AMM) Task 20-28-00-720-006

Fig. A-UAAAA

Inspection Flow Chart

Sheet 01

Refer to Fig. A-UAAAA Sheet 01

(a) Do a bonding test from the adaptor FIN 42QM and FIN 43QM to the wing skin

panels (Refer to AMM Task 20-28-00-720-006).

(b) If the resistance value is 10 milliOhms or less at the LH wing and the RH wing, no

more work is necessary. Go to SUBTASK 571152-942-401 001 Close-up .

(c) If the resistance value is greater than 10 milliOhms at the LH wing and/or the RH

wing, do the worksteps that follow.

(2) Subtask 571152-832-401-001 - Removal of Primer - Inspection for Corrosion

Work Zones and Access Panels

Zone Access/Work location

540 Work location FIN 42-QM

640 Work location FIN 43-QM

Manpower Resources

Manhours 5.0

Minimum number of person 2

Subtask elapsed time 2.5

Skills AIRFRAME

Material necessary to do the job

Consumable CMLB01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Solvent General Purpose 11-026 As required

Chemical Conversion

Coating Yellow Aluminum

13-002 As required

Lint-Free Cotton Cloth 19-003 As required

References

Aircraft Maintenance Manual (AMM) 28-11-43, Page Block 401

Fig. A-UAAAA

Inspection Flow Chart

Sheet 01

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References

Fig. A-UACAA

Inspection for Corrosion after Removal

of Primer

Sheet 01

Refer to Fig. A-UAAAA Sheet 01 and to Fig. A-UACAA Sheet 01

(a) Remove the applicable gravity fill cap/adaptor FIN 42QM and/or FIN 43QM (Refer

to AMM 28-11-43, Page Block 401).

NOTE: The above AMM reference gives instructions to defuel and vent the

wing fuel tanks and to remove the applicable manhole covers.

(b) Remove the paint/primer from the rim of the aperture for the gravity fill adaptor in

the top skin panel with abrasive paper grade 320, Fig. A-UACAA Sheet 01 Section

A-A.

(c) Clean the mating surfaces back to bare metal, use:

Lint-Free Cotton

Cloth

19-003 As required

made moist with:

Solvent General

Purpose

11-026 As required

(d) Do an inspection of the component interface and/or adjacent area.

(e) If the inspection shows defects on the aperture flange, before completing the steps

that follow, go to SUBTASK 571152-833-401 001 Repair .

(f) If there are no defects, apply:

Chemical

Conversion Coating

Yellow Aluminum

13-002 As required

to the area shown.

(g) Install the applicable gravity fill cap/adaptor FIN 42QM and/or FIN 43QM (Refer to

AMM 28-11-43, Page Block 401).

NOTE: It will not be necessary to remove paint from the component

interface or apply Mat. No 13-002 as detailed in the AMM 28-11-43,

Page Block 401 reference under Preparation for Installation, as

these worksteps are included in para. (b) and (f) above.

NOTE: The AMM 28-11-43, Page Block 401 reference for installation of the

gravity fill cap/adaptor includes a bonding check, if the bonding

resistance is greater than 10 milliOhms, repeat SB accomplishment

instructions or contact AIRBUS for instructions.

NOTE: The above AMM reference gives instructions to install the applicable

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manhole covers and refuel the wing fuel tanks as necessary.

(3) Subtask 571152-833-401-001 - Repair

Manpower Resources

Manhours 6.0

Minimum number of person 2

Subtask elapsed time 3.0

Skills AIRFRAME

References

Structural Repair Manual (SRM) 51-74-00

57-21-11 Page Block 101

57-21-11

Fig. A-UACAA

Inspection for Corrosion after Removal

of Primer

Sheet 01

(a) Remove any signs of corrosion (Refer to SRM 51-74-00).

(b) Refer to SRM 57-21-11 for allowable damage and repair instructions.

NOTE: SRM 57-21-11 is in the process of revision to include allowable

damage and repair instructions for this area. AIRBUS should be

contacted for Repair Instruction and RAS prior to the SRM revision.

(c) If no SRM allowable damage and repair instructions are available, contact AIRBUS

before next flight to get an approved repair.

D. TEST

None

E. CLOSE-UP

(1) Subtask 571152-942-401-001 - Close-up

Work Zones and Access Panels

Zone Access/Work location

540 Work location from Rib 19 to Rib 20

640 Work location from Rib 19 to Rib 20

Manpower Resources

Skills NON SPECIFIC

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

equipment.

(b) Move the access platforms clear of the aircraft.

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**CONF ALL

NO FURTHER

ACTION

RESISTANCE

VALUE 10 milliOhms

OR LESS?

AT OR BEFORE 24 MONTHS FROM THE

ISSUE DATE OF THIS SERVICE

BULLETIN, DO AN ELECTRICAL BONDING

YES NO

INSPECTION

SHOW DEFECTS ON

THE APERTURE

FLANGE?

CHECK OF THE GRAVITY FILL ADAPTOR

REMOVE THE GRAVITY

FILL ADAPTOR REF AMM

NO

SEAL AND REINSTALL

THE GRAVITY FILL

ADAPTOR REF AMM

RE−PROTECT SURFACES,

BONDING CHECK OF THE

GRAVITY FILL ADAPTOR

REF AMM

DO AN ELECTRICAL

YES

IS SRM

ALLOWABLE DAMAGE

AND REPAIRS

AVAILABLE?

YES

NO

BEFORE

NEXT FLIGHT FOR

APPROVED REPAIR

CONTACT AIRBUS

BEFORE NEXT FLIGHT

PERFORM SRM REPAIR

AND REINSTALL

GRAVITY FILL

ADAPTOR

REF AMM

NOTE: TO ENSURE CONSERVATIVE COVERAGE AT AIRCRAFT LEVEL, THE ABOVE

INSPECTION PROCEDURE SHOULD BE PERFORMED ON BOTH WINGS OF THE

IDENTIFIED AIRCRAFT. N_SB_571152_7_AAAA_01_11

CLEAN OFF MATING SURFACES

BACK TO BARE METAL.

REF: FIGURE A−UACAA

SHEET 01 SECTION A−A

AND AMM

DO AN INSPECTION

OF THE COMPONENT

INTERFACE REF AMM

DID THE

Figure A-UAAAA - Sheet 01

Inspection Flow Chart

DATE: Jun 14/10 SERVICE BULLETIN No.: A320-57-1152

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**CONF ALL

RIB19

RIB20

540PB

(640PB)

A

CAP

LANYARD

O−RING ADAPTOR

ADAPTOR

WING SKIN PANEL No. 2

FLANGE

B

3 TO 5 mm (0.118 TO 0.196 in)

PAINT/PRIMER REMOVED.

CAP

ADAPTOR

WING

SKIN

O−RINGS

(REF. ONLY)

FRONT

SPAR

LINE OF

FLIGHT

GRAVITY FILL

CAP/ADAPTOR

APERTURE

A A

RIB19

44QM

(45QM)

42QM

(43QM)

A

B

N_SB_571152_7_ACAA_01_01

A A

Figure A-UACAA - Sheet 01

Inspection for Corrosion after Removal of Primer

DATE: Jun 14/10 SERVICE BULLETIN No.: A320-57-1152

REVISION No.: 00 - Jun 14/10 Page: 15

7

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A318/A319/A320/A321

SERVICE BULLETIN

REPORTING SHEET

TITLE: WINGS - OUTER WING - REFUEL APERTURE - INSPECTION OF

ELECTRICAL BONDING

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: Jun 14/10 SERVICE BULLETIN No.: A320-57-1152

REVISION No.: 00 - Jun 14/10 Page: 1

7

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A318/A319/A320/A321

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: Jun 14/10 SERVICE BULLETIN No.: A320-57-1152

REVISION No.: 00 - Jun 14/10 Page: 1

7

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.