@A300

SERVICE BULLETIN

SUMMARY

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX

FRANCE

Tel : (33) 5 61 93 33 33

Telex : AIRBU 530526F

Fax : (33) 5 61 93 42 51

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

MANDATORY MANDATORY MANDATORY

ATA SYSTEM: 53

TITLE: FUSELAGE - FUSELAGE TAIL SECTION AND TAIL CONE FR80-FR103

- REINFORCE THS SUPPORT STRUTS AT FR91 BY CLAMPS

**CONF ALL

MODIFICATIONS

MODIFICATION CLASSIFICATION

MAJOR 13682D23322

MINOR None

NOTE: As per EASA IR 21, a minor change is one that has no appreciable effect on the

mass, balance, structural strength, reliability, operational characteristics affecting the

airworthiness of the product. All other changes are major changes.

REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

The Trimmable Horizontal Stabilizer (THS) is supported and articulated at Frame 91. Any lateral

movement is prevented by four diagonal support struts.

During maintenance, support struts have been found cracked on some aircraft.

The affected area is the strut end and typical cracks are longitudinal. On some aircraft, several cracks

per support strut have been found.

Inspection Service Bulletin A300-53-0395 inspects the struts for cracks.

This Service Bulletin installs reinforcing clamps on the strut ends as a temporary solution. A permanent

solution is expected to be introduced by Service Bulletin at a later date.

By installing the clamp, the circumferential stresses in the rod-ends are reduced and the circular shape

of the rod end is supported.

As a result, the tendency to stress corrosion of the rod ends is stopped (or partially reduced) due to the

lower circumferential stresses.

Furthermore, the steel insert in the rod ends is properly kept in place due to maintaining the circular

shape of the rod ends even in case of existing cracks.

DATE: Feb 14/14 SERVICE BULLETIN No.: A300-53-0394

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SERVICE BULLETIN

SUMMARY

Depending on the result of the check (aircraft record or physical check) required in inspection Service

Bulletin A300-53-0395, it is possible that clamps installation is not required on one or some struts

(mixture of clamp installation is possible).

GENERAL EVALUATION

EVALUATION TABLE

COMPLIANCE MANDATORY (1) CANCELS INSPECTION SB NO

POTENTIAL AD YES A/C OPERATION AFFECTED NO

RELIABILITY AFFECTED NO PAX COMFORT AFFECTED NO

COST SAVING NO ETOPS AFFECTED NO

STRUCTURAL LIFE EXTN NO VENDOR SB INVOLVED NO

NOTE (1): Service Bulletin must be accomplished.

MATERIAL PRICE INFORMATION

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Kit 530394D01R00 1 2,100.00 Clamps

EFFECTIVITY

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

001 50W 81T ABR AFG F2I IAW IRA IRM KZU MNB MSR RUN

SOP TIW TNO TSY

CONCURRENT REQUIREMENTS

Accomplishment of this Service Bulletin requires the prior or simultaneous accomplishment of the

following Service Bulletin(s) as per effectivity specified in this (these) Service Bulletin(s):

Service Bulletin No. A300-53-0395

NOTE: A300-53-0395 FUSELAGE - TAIL CONE - THS SUPPORT STRUTS AT FR91 -

INSPECTION FOR CRACKS

REFERENCES / REPERCUSSIONS

TFU 53.19.89.001

OEB None

AOT None

SIL None

LINE MAINTENANCE AFFECTED No

LIFE LIMIT None

OTHER None

NATURE OF THE WORK

AIRCRAFT YES

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SERVICE BULLETIN

SUMMARY

EQUIPMENT NO

HARD NO

SOFT NO

OBRM NO

MANPOWER

Task 530394-831-848-001: Modification

TOTAL MANHOURS 2.00

ELAPSED TIME (HOURS) 2.00

APPENDICES

None

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SERVICE BULLETIN

SUMMARY

**CONF ALL

FR91

A

B

B

B

B

Z310

A

TYPICAL

CLAMP TO

BE ADDED

CLAMP TO

BE ADDED

B

A_SB_530394_6_SAAA_01_01

Figure A-GSAAA - Sheet 01

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@A300

SERVICE BULLETIN

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX

FRANCE

Tel : (33) 5 61 93 33 33

Telex : AIRBU 530526F

Fax : (33) 5 61 93 42 51

MANDATORY MANDATORY MANDATORY

ATA SYSTEM: 53

TITLE: FUSELAGE - FUSELAGE TAIL SECTION AND TAIL CONE FR80-FR103

- REINFORCE THS SUPPORT STRUTS AT FR91 BY CLAMPS

MODIFICATION No.: 13682D23322

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

Kit 530394D01R00 is only applicable on aircraft on which specific struts with PN R21449, PN

R21449D, PN R21449G or PN R21449H are installed.

This modification is applicable by Service Bulletin only.

(1) Models

B2-1C B2-203 B2K-3C B4-103 B4-203 B4-2C C4-203 F4-203

(2) Effectivity by MSN

0003 0041 0045 0055 0075 0080 0090 0101 0105 0107 0117 0123 0126 0129 0139

0151-0152 0154 0157 0160 0173 0175 0180 0183 0185 0187 0200 0203-0204 0210

0212 0218 0220 0226-0227 0234-0236 0239 0244 0247 0255-0256 0259 0261 0274

0277 0292 0299 0302 0304

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SERVICE BULLETIN

(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

001 0203 0218

50W 0003

81T 0157 0277 0292

ABR 0152 0220 0234 0236 0259 0274

AFG 0180

F2I 0235

IAW 0239

IRA 0080 0139 0151 0173 0185 0187 0226 0256 0299 0302

IRM 0055 0090 0160 0175 0204 0244

KZU 0041 0101 0117

MNB 0123 0212 0304

MSR 0200 0255

RUN 0075 0105 0107 0154 0183

SOP 0126

TIW 0261

TNO 0045 0210 0227 0247

TSY 0129

(4) Configuration by MSN

MSN CONFIGURATION

0003 0041 0045 0055 0075 0080 0090 0101 0105 0107 0117

0123 0126 0129 0139 0151 0152 0154 0157 0160 0173 0175

0180 0183 0185 0187 0200 0203 0204 0210 0212 0218 0220

0226 0227 0234 0235 0236 0239 0244 0247 0255 0256 0259

0261 0274 0277 0292 0299 0302 0304

001

(5) Configuration definition

**CONF 001

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

standard configuration.

(6) Material Effectivity

MATERIAL QTY PER A/C SEE NOTES

Kit 530394D01R00 1

Consumable CMLD01 As required

B. CONCURRENT REQUIREMENTS

Accomplishment of this Service Bulletin requires the prior or simultaneous accomplishment of

the following Service Bulletin(s) as per effectivity specified in this (these) Service Bulletin(s):

DATE: Feb 14/14 SERVICE BULLETIN No.: A300-53-0394

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SERVICE BULLETIN

Service Bulletin No. A300-53-0395

NOTE: A300-53-0395 FUSELAGE - TAIL CONE - THS SUPPORT STRUTS AT FR91

- INSPECTION FOR CRACKS

C. REASON

(1) History

The Trimmable Horizontal Stabilizer (THS) is supported and articulated at Frame 91.

Any lateral movement is prevented by four diagonal support struts.

During maintenance, support struts have been found cracked on some aircraft.

The affected area is the strut end and typical cracks are longitudinal. On some aircraft,

several cracks per support strut have been found.

Inspection Service Bulletin A300-53-0395 inspects the struts for cracks.

(2) Objective/Action

This Service Bulletin installs reinforcing clamps on the strut ends as a temporary

solution. A permanent solution is expected to be introduced by Service Bulletin at a later

date.

(3) Advantages

By installing the clamp, the circumferential stresses in the rod-ends are reduced and the

circular shape of the rod end is supported.

As a result, the tendency to stress corrosion of the rod ends is stopped (or partially

reduced) due to the lower circumferential stresses.

Furthermore, the steel insert in the rod ends is properly kept in place due to maintaining

the circular shape of the rod ends even in case of existing cracks.

(4) Operational/Maintenance Consequences

Depending on the result of the check (aircraft record or physical check) required in

inspection Service Bulletin A300-53-0395, it is possible that clamps installation is not

required on one or some struts (mixture of clamp installation is possible).

D. DESCRIPTION

To accomplish this Service Bulletin it is necessary to :

Task 530394-831-848-001: Modification

(1) Install the clamps at the THS support struts

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SERVICE BULLETIN

E. COMPLIANCE

(1) Classification

MANDATORY: Service Bulletin must be accomplished.

(2) Accomplishment Timescale

This Service Bulletin must be accomplished, when applicable, immediately after the first

inspection in accordance with the Inspection Service Bulletin A300-53-0395 requirement.

This Service Bulletin has been classified Mandatory by the issue of an Airworthiness

Directive (AD) published by the European Aviation Safety Agency (EASA). The AD must

be used as the reference document for the mandated accomplishment timescale.

F. APPROVAL

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

Organisation Approval No. EASA.21J.031.

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

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

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

before incorporation of the Service Bulletin.

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 530394-831-848-001: Modification

Get Access 0.50

On Aircraft

Install the clamps at the THS support struts 1.00

Close-Up 0.50

TOTAL MANHOURS 2.00

ELAPSED TIME (HOURS) 2.00

H. WEIGHT AND BALANCE

The weight and balance estimates given in this Service Bulletin are based on the

Manufacturer’s Empty Weight (MEW) and do not include operator items. For the definition of

MEW and operator’s items refer to Weight and Balance Manual (WBM) Chapter 1-00-07.

Manufacturers Empty Weight +2.198 KG (+4.8457 LB)

Effect on Balance +120.824 KGM (+873.919 LB.FT )

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SERVICE BULLETIN

I. ELECTRICAL LOAD DATA

Not Changed

J. REFERENCES

Aircraft Maintenance Manual (AMM) 06-21-00 06-21-53 20-21-12

24-00-00 53-00-00

Consumable Material List (CML)

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

Service Bulletin (SB) A300-53-0395

Standards Manual (SM)

Structural Repair Manual (SRM) 51-30-29 51-30-31 51-40-20

Weight and Balance Manual (WBM) Chapter 1-00-07

K. PUBLICATION AFFECTED

Aircraft Maintenance Manual (AMM) 53-22-14 53-46-00 53-46-11

Illustrated Parts Catalog (IPC) 53-46-04

L. INTERCHANGEABILITY/MIXABILITY

Not Applicable

M. SPARES

None

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SERVICE BULLETIN

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SERVICE BULLETIN

2. MATERIAL INFORMATION

**CONF ALL

A. MATERIAL - PRICE AND AVAILABILITY

(1) Procurement Addresses

This Service Bulletin is the subject of an AIRBUS monitored retrofit campaign.

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:

NOTE: Kit 530394D01R00 is only applicable on aircraft on which specific struts

with PN R21449, PN R21449D, PN R21449G or PN R21449H are

installed.

Kit 530394D01R00 AIRBUS Material, Logistics and Suppliers

Weg beim Jaeger 150

D-22335 HAMBURG

GERMANY

For ordering by internet:

http://spares.airbus.com

For ordering by fax: +49 40 50 76 2590

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

(2) Price and Availability

Kit 530394D01R00

Cost 2,100.00 USD

Availability 120 calendar days from receipt of order

The availability given above is the standard lead time from the date of your purchase

order. If items are required 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. 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

As a special policy applied to this Service Bulletin, AIRBUS will provide a 10% reduction to

the applicable kits sales prices given in the paragraph Price and Availability for orders placed

before Dec 31/19.

For the organisation of this retrofit, you are kindly requested to contact AIRBUS retrofit

management department.

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX

France

DATE: Feb 14/14 SERVICE BULLETIN No.: A300-53-0394

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SERVICE BULLETIN

E-mail : monitored.retrofit@airbus.com

Tel : (33) 5 67 19 06 22

Fax : (33) 5 61 93 27 45

C. LIST OF COMPONENTS

Kit 530394D01R00

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

NOTES

1 A5347310320000 16 CLAMP

2 NSA5031-5-38 16 BOLT

3 NAS1149D0563K 16 WASHER

4 NAS1726-5E 16 NUT

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.

NOTE: Kit 530394D01R00 is only applicable on aircraft on which specific struts with

PN R21449, PN R21449D, PN R21449G or PN R21449H are installed.

D. LIST OF MATERIALS - OPERATOR SUPPLIED

(1) Consumable Materials

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO CML

MAT. No.

QTY PER A/C SEE

NOTES

Coating-- Flexible Structure 04QAB2 As required

Polysulfide Sealant-Low Adhesion

Fillet Structure

06AEB2 As required

Non Hardening Jointing Putty-High

Temp. Area Str

06LDG2 As required

Corrosion Preventive CompoundWater Displacing12ADB1 As required

(2) Components

None

(3) Equipment

None

E. PARTS TO BE RE-IDENTIFIED BY OPERATOR

None

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SERVICE BULLETIN

F. TOOLING

None

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SERVICE BULLETIN

3. ACCOMPLISHMENT INSTRUCTIONS

Task 530394-831-848-001 - Modification

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, REFER TO ESPM 20-55-00.

NOTE: The accomplishment instructions of this Service Bulletin refer to procedures

included in other AIRBUS documents. When the words ’refer to’ are used and the

operator has an accepted alternative procedure, the accepted alternative procedure

can be used. When the words ’in accordance with’ are included in the instruction,

the procedure in the AIRBUS document must be used.

NOTE: The access and close-up instructions, not comprising return to service tests, in this

Service Bulletin do not constitute or affect the technical intent of the Service

Bulletin. Operators can therefore, as deemed necessary, omit or add access and/or

close-up steps to add flexibility to their maintenance operations as long as the

technical intent of the Service Bulletin is met within the set parameters.

NOTE: Manual titles given in the accomplishment instructions are referred to by acronyms.

Refer to paragraph 1.J., References, for the definition of acronyms.

NOTE: This Service Bulletin is classified mandatory or expected to be classified mandatory

by an Airworthiness Directive (AD). The paragraphs 3.C. and 3.D. in these

accomplishment instructions are Required for Compliance (RC) and must be done

to comply with the AD. Other paragraphs are recommended and may be deviated

from, done as part of other actions or done with accepted methods different from

those given in the Service Bulletin, as long as the RC paragraphs can be done and

the aircraft can be put back into a serviceable condition.

Task Associated Data

Zone

310

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SERVICE BULLETIN

Access

Door 313AL

Manpower

TOTAL MANHOURS 2.00

ELAPSED TIME (HOURS) 2.00

A. GENERAL

(1) Subtask 530394-910-201-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-21-00, Page Block 001

06-21-53, Page Block 001

20-21-12, Page Block 001

53-00-00, Page Block 001

Consumable Material List (CML)

Structural Repair Manual (SRM) 51-30-29

51-30-31

51-40-20

(a) For the specification of materials (Mat. No.) given in this Service Bulletin, refer to

the Consumable Materials List (CML).

(b) For the Frame (FR) identification , refer to AMM 53-00-00, Page Block 001.

(c) For the identification of zones, refer to AMM 06-21-00, Page Block 001.

(d) For the identification of access panels, refer to AMM 06-21-53, Page Block 001.

(e) Torque tighten the standard threaded fasteners, refer to AMM 20-21-12, Page

Block 001.

(f) Remove and install fasteners in accordance with SRM 51-30-29.

(g) Apply sealant in accordance with SRM 51-40-20.

(h) Obtain alternative and substitute fastener data in accordance with SRM 51-30-31.

(i) If alternative and substitute fasteners have to be used, you must make sure that the

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

column.

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

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

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

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

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

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SERVICE BULLETIN

(2) Subtask 530394-839-201-001 - 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 530394-941-201-001 - Job Set-up

Work Zones and Access Panels

Zone Access/Work location

310 Access Door 313AL

Work location Frame 91

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 24-00-00, Page Block 301

(a) The following items shall be considered as the basic Aircraft configuration before

you start a maintenance task:

- Aircraft on the ground resting on landing gear (the ground safety locks and the

wheel chocks are in position on the landing gear).

- Engine shut down, thrust reversers closed and locked.

- Aircraft in clean configuration.

- Parking brake applied.

- Aircraft electrical network de-energized.

- Hydraulic systems depressurized.

- Access to the cockpit and cabin is available.

- All circuit breakers are in closed position.

- All controls in NORM, AUTO or OFF position.

(b) Make sure that the aircraft is electrically grounded, refer to AMM 24-00-00, Page

Block 301.

(c) Put the access platform(s) in position below the access door 313AL.

(d) Open access door 313AL.

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SERVICE BULLETIN

C. PROCEDURE

(1) Subtask 530394-420-201-001 - Install the clamps at the THS support struts

Work Zones and Access Panels

Zone Access/Work location

310 Work location Frame 91

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills AIRFRAME

Material necessary to do the job

Kit 530394D01R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 A5347310320000 16 CLAMP

2 NSA5031-5-38 16 BOLT

3 NAS1149D0563K 16 WASHER

4 NAS1726-5E 16 NUT

NOTE: Kit 530394D01R00 is only applicable on aircraft on which specific struts

with PN R21449, PN R21449D, PN R21449G or PN R21449H are

installed.

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Coating-- Flexible Structure 04QAB2 As required

Polysulfide Sealant-Low

Adhesion Fillet Structure

06AEB2 As required

Non Hardening Jointing

Putty-High Temp. Area Str

06LDG2 As required

Corrosion Preventive

Compound-Water

Displacing

12ADB1 As required

References

Fig. A-GBAAA

Installation of the Clamps at the THS

Support Struts

Sheet 01

(a) Apply:

Refer to Fig. A-GBAAA Sheet 01, View C.

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SERVICE BULLETIN

Polysulfide SealantLow Adhesion Fillet

Structure

06AEB2 As required

to the interface surfaces of the clamps, Item 1.

NOTE: Application of the sealant is required at the interfaces between the

two clamp halves and at the interfaces between the clamps and the

support struts.

(b) Apply to the bolts, Item 2:

Refer to Fig. A-GBAAA Sheet 01, View C.

Non Hardening

Jointing Putty-High

Temp. Area Str

06LDG2 As required

and install:

Refer to Fig. A-GBAAA Sheet 01, Views A to D.

NOTE: Consider that the clamps must be installed within the cylindrical

area only.

NOTE: Make sure that the dimension of the gap is between 3.0 mm and

3.5 mm (0.118 in and 0.138 in).

NOTE: Before installation of the clamp, mark the correct position with a

pen.

16 Clamp A5347310320000 Item 1

with:

16 Bolt NSA5031-5-38 Item 2

16 Washer NAS1149D0563K Item 3

16 Nut NAS1726-5E Item 4

(c) Protect the visible edges of the sealant, 06AEB2, with:

Coating-- Flexible

Structure

04QAB2 As required

(d) On the clamps and fasteners which you have installed, apply:

Corrosion

Preventive

Compound-Water

Displacing

12ADB1 As required

DATE: Feb 14/14 SERVICE BULLETIN No.: A300-53-0394

REVISION No.: 00 - Feb 14/14 Page: 15

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SERVICE BULLETIN

D. TEST

None

E. CLOSE-UP

(1) Subtask 530394-942-201-001 - Close-up

Work Zones and Access Panels

Zone Access/Work location

310 Access Door 313AL

Work location Frame 91

Manpower Resources

Skills NON SPECIFIC

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

equipment.

(b) Close the access door 313AL.

(c) Remove the access platform(s).

DATE: Feb 14/14 SERVICE BULLETIN No.: A300-53-0394

REVISION No.: 00 - Feb 14/14 Page: 16

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SERVICE BULLETIN

**CONF ALL

C

C

FR91

TYPICAL

D

1

2

3

4 C

B

A

D

B

B

B

B

Z310

A

3.0 mm TO 3.5 mm

(0.118 in TO 0.138 in)

D

2

3

4

1

01 PROTECT WITH COMPOUND (MAT. NO. 12ADB1)

02 CONSIDER THAT THE CLAMPS MUST BE INSTALLED

NOTE:

01

02

WITHIN THE CYLINDRICAL AREA ONLY A_SB_530394_6_BAAA_01_03

Figure A-GBAAA - Sheet 01

Installation of the Clamps at the THS Support Struts

DATE: Feb 14/14 SERVICE BULLETIN No.: A300-53-0394

REVISION No.: 00 - Feb 14/14 Page: 17

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SERVICE BULLETIN

REPORTING SHEET

TITLE: FUSELAGE - FUSELAGE TAIL SECTION AND TAIL CONE FR80-FR103

- REINFORCE THS SUPPORT STRUTS AT FR91 BY CLAMPS

MODIFICATION No.: 13682D23322

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: Feb 14/14 SERVICE BULLETIN No.: A300-53-0394

REVISION No.: 00 - Feb 14/14 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: Feb 14/14 SERVICE BULLETIN No.: A300-53-0394

REVISION No.: 00 - Feb 14/14 Page: 1

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