EASA

EASA AD No : 2010-0007

AIRWORTHINESS DIRECTIVE

AD No.: 2010-0007

Date: 07 January 2010

Nole: This Airworthiness Directive (AD) is issued by EASA, acting in acco«lance with

Regulation (Ee) No 21612008 on behal! 01 the European Community. its Member Stales and of

the European third co"nlries Ihal participate in Ihe activities of EASA under Article 66 of thai

Regulation.

AIRBUS

Type Approval Holder's Name:

This AD is issued in accordance with EC 170212003, Part 21A.38. in accordance with EC 2042/2003 Annex I, Part MA301, the

continuing airworthiness of an aircraft shall be ensured by accomplishing' any applicable ADs. Consequently, no person may operate

an aircraft 10 which an AD applies, except in accordance with the requirements 01 that AD. unless otherwise specified by the Agerlcy

lEG 2042/2003 Annex I. Part M.A.303] or agreed with the Authority of IheiStat8 of Registry lEG 216/2008. Article 14(4) exemptionJ.

I

iype/MOdel designation(s) :

A300-600 aeroplanes

TCDS Number:

Foreign AD :

Supersedure:

ATA 53

Manufacturer(s):

Applicability:

Reason:

Effective Date:

France No. 145

Not applicable

None

Fuselage - Frame 58 Butt Joint - Reinforcement

Airbus (formerly Airbus lndus+e)

A300B4-601, A300B4-603, AdoOB4-605R, A300B4-620, A300B4-622,

A300B4-622R, A300C4-605Rlvariant F, A300C4-620 and A300F4-605R premod 12699 aeroplanes, all serial numbers.

Note: For A300F4-605R post-mod 12699 and A300F4-622R aeroplane

models, whose Limit of Validity is 30 000 Flight Cycles (FC), the requirements

of this AD do not apply.

A recent Wide spread Fatigue Damage (WFD) calculation on A300-600

aeroplanes has shown that a reinforcement of the upper fuselage

circumferential joint at FR 58 is necessary to enable the aeroplane to reach

the Extended Service Goal (ESG).

The failure of the circumferential joint of the upper fuselage could affect the

structural integrity of the aeroplane.

For the reasons described above, this AD requires the reinforcement of the

affected fuselage frame butt joint.

21 January 2010

'E"A"S"ACF"oO,=m"'"Co;-----------------,---------------",p:,:ge:-;1"r'
EASA

EASA AD No . 2010-0007

AIRWORTHINESS DIRECTIVE

AD No.: 2010~007

Date: 07 January 2010

Note: This Airworthiness Directive (AD) is issued by EASA, acting in accordance with

Regulation (EG) No 21612008 on behalf of the Europe;:!n Community, its Member Stales and of

\he European third countries that pMicipale in the aGlivilies of EASA under Article 66 01 that

Regulation.

This AD is issued in accordance with EC 170212003, Part 21A.3B. In accordance with EC 2042/2003 Annex I, Part MAW1, the

continuing airworthiness of an aircraft shall be ensured by accomplishing1any applicable ADs. Consequently, no person may operate

an aircrafllQ which an AD applies, except in accordance with the require(Tlenls of thai AD, unless otherwise specified by the Agency

[EG 204212003 Annex I. Part M.A.303] or agreed with the Authority of the plate of Registry [EG 21612008, Article 14(4) exemption].

Type Approval Holder's Name:

AIRBUS

I

ljypefModel designation(s) :

I

A300-600 aeroplanes

TeDS Number:

Foreign AD :

Supersedure:

ATA53

Manufacturer(s):

Applicability:

Reason:

Effective Date:

EASA Form 110

France No. 145

Not applicable

None

Fuselage - Frame 58 Butt Joint - Reinforcement

Airbus (fonnerly Airbus Indus+e)

A300B4-601, A300B4-603, AdoOB4-605R, A300B4-620, A300B4-622,

A300B4·622R, A300C4-605Rlvariant F, A300C4-620 and A300F4-605R pre-

:::: ::~:;::~~~;;;~ a~~::J:~:~::::s~nd A300F4-622R aeroplane

models, whose Umit of ValiditY is 30 000 Flight Cycles (FC), the requirements

of this AD do not apply.

A recent Wide spread Fatigue Damage (WFD) calculation on A30o-600

aeroplanes has shown that a reinforcement of the upper fuselage

circumferential joint at FR 58 is necessary to enable the aeroplane to reach

the Extended Service Goal (ESG).

The failure of the circumferential joint of the upper fuselage could affect the

structural integrity of the aeroplane.

For the reasons described above, this AD requires the reinforcement of the

affected fuselage frame butt joint.

21 January 2010

Page 1/2
EASA AD No: 2010-0007

Required as indicated, unless already accomplished:

Required Action(s) Before accumulation of 42 500 FC, or within 2 000 FC after the effective date

and Compliance of this AD, whichever occurs later, reinforce the fuselage butt joint at FR 58 in

Time(s): accordance with the accomplishment instructions of Airbus Service Bulletin

(SB) A30Q-53-6146 Revision 01.

Airbus SB A300-53-6146 Revision 01.

Ref. Publications: The use of later approved revisions of this document is acceptable for

compliance with requirements of this AD.

1. If requested and appropriately substantiated, EASA can approve

Alternative Methods of Cbmpliance for this AD.

2. This AD was posted on O~Augusl2009 as PAD 09-016 for consultation

until 02 September. The Comment Response Document can be found at

http://ad.easa.euro pa .eull

Remarks: I

3. Enquiries regarding this 10 should be referred to the Airworthiness

Directives, Safety Manag~ment & Reseal"ch Section, Certification

Directorate, EASA. E-mail ADs@easa.europa.eu.

4. For any question concerning the technical content of the requirements in

this AD, piease contact: AIRBUS SAS - EAW Airworthiness Office,

telephone: + 33 5 61 93 3696, facsimile: + 33 5 61 9344 51.

EASA Form 110 Page 2/,2