EASA AD No.: 2013

- 0295

TE.CAP.00110

- 00 3 © European Aviation Safety Agency. All rights reserved. 1 / 4 Proprietary document. Copies are not control led. Confirm revision status through the EASA

- Internet/Intranet. 

## EASA AIRWORTHINESS DIRECTIVE

AD No

. : 2013

- 0295

Date: 1 1 December 2013

Note: This Airworthiness Directive (AD) is issued by EASA, acting in accordance with Regulation (EC) No 216/2008 on behalf of the European Community, its Member States and of the European third countries that participate in the activities of EASA under Article 66 of that Regulation.
This AD is issued in accordance with EU 748/2012, Part 21.A.3B. In accordance with EC 2042/2003 Annex I, Part M.A.301, the continuing airworthiness of an aircraft shall be ensured by accomplishing any applicable ADs. Consequently, no person may operate an aircraft to which an AD applies, except in accordance with the requirements of that AD, unless otherwise specified by the Age ncy [EC 2042/2003 Annex I , Part M.A.303] or agreed with the Authority of the State of Registry [EC 216/2008, Article 14(4) exemption]. 

### Design Change Approval Holder’s Name : AIRBUS Type/Model designation(s) : A 300

- 600 aeroplanes

TCDS Number: France No

. 145

F oreign AD: Not applica ble
Supersedure: This AD supersedes DGAC France AD F

- 200 4

- 002 ( EASA approval 200 3

- 2108 )

da ted 07 January 2004.



### ATA 5 3 Fuselage

– Center Section Frame s and Stringer s – Inspection / Modification

Manufacturer(s): Airbus ( f orme r ly Airbus Industrie)

Ap plicability: Airbus A300

- 600 aeroplanes, all certified models except model A300F4

- 622R
, all manufacturer serial numbers

.
Reason: During a scheduled inspection of the fuselage frame feet of an in

- service A300

- 600 aeroplane, cracks w ere observed in Frame ( FR ) 43, FR 44, FR 45 and FR 46 between stringer ( STGR ) 24 and STGR 30. This condition, if not detected and corrected, could affect the structural integrity of the aeroplane. To address this unsafe condition, DGAC France issued AD 2000

- 060

- 303 (later revi sed) to require repetitive inspections of the affected frames and stringers on both sides of the fuselage and, depending on findings, repairs, as specified in Airbus Service Bulletin (SB) A300

- 53

- 6122

. Subsequently , DGAC France issued AD F

- 2004

- 002 ( EASA a pproval 200 3

- 2108 )
, retaining the requirements of AD 2000

- 060

- 303 R1, which was superseded, and required the embodiment of Airbus SB A300

- 53

- 6125 (Airbus modification 12168) in order to improve the life of the frame foot attachment.
Since DGAC France AD F

- 200 4

- 00 2 was issued, a fleet survey and updated Fatigue and Damage Tolerance analyses were performed in order to substantiate the second A300

- 600 Extended Service Goal (ESG2) exercise.
I t w as highlighted that the frame feet material change from 2024T351 1 (A300B4) to 7175T7351 (A300

- 600) had an impact on the frame feet fatigue life duration. Airbus SB A300

- 53

- 6 1 22 was revised accordingly to decreas e theEASA AD No.: 2013

- 0295

TE.CAP.00110

- 00 3 © European Aviation Safety Agency. All rights reserved. 2 / 4 Proprietary document. Copies are not control led. Confirm revision status through the EASA

- Internet/Intranet. inspection thresholds and intervals. Subsequent SB revision introduce d a second s tructural m odification p oint (SMP2) for a eroplane s that embody Airbus SB A300

- 53

- 6125 ( modification 12168)

. For the reasons described above, this new AD retains the requirements of DGAC France AD F

- 200 4

- 00 2, which is superseded, but requires th os e actions within the new thresh olds and intervals as specified in Revision 04 of Airbus SB A300

- 5 3

- 6122

.

Effective Date: 2 5 December 2013

Required A ction(s) and Compliance Time(s) : Required as indicated, unless previously accomplished:
INSPECTION: (1) Within the compliance time defined i n Table 1 of this AD, as applicable depending on aeroplane configuration and Average Flight Time (AFT), and, thereafter, at intervals not to exceed those defined in Table 2 of this AD, accomplish a rotating probe inspection of the frame feet attachment hol es of FR 41 to FR 46 in accordance with the instructions of Airbus SB A300

- 53

- 6122

. Note: For the purpose of this AD, the AFT shall be established as follows for the determination of:

- The inspection threshold ( TH ) , as the t otal accumulated flight hours ( FH ), counted from take

- off to touch

- down
, divided by the total accumulated flight cycles ( FC ) at the effective date of this AD.

- The first inspection interval ( INT ) , as the total accumulated FH divided by the total accumulated FC at the time of the TH inspection

.

- The second inspection INT onwards, as the FH divided by the FC accumulated between the last two inspections.

Table 1 : Inspection t hres h olds ( whichever occurs first
, FH or FC )

Aeroplane configuration AFT > 1,5 FH/FC AFT ≤ 1,5

FH/FC Aeropla nes on which Airbus SB A300

- 53

- 6125 has not been accomplished (threshold counted since aeroplane first flight ) 14 800 FH 6 800

FC 11 100

FH 7 400

FC

Aeroplanes on which Airbus SB A300

- 53

- 6125 has been accomplished (threshold counted from the date of accomplishment of SB A300

- 53

- 6125 ) 56 400 FH 26 100

FC 42 300

FH 28 200

FC

Aeroplanes on which Airbus SB A300

- 53

- 6125 SMP2 has been accomplished (threshold counted from the date of accomplishment of SB A300

- 53

- 6125 ) 69 400 FH 32 100

FC 52 000

FH 34 700

FCEASA AD No.: 2013

- 0295

TE.CAP.00110

- 00 3 © European Aviation Safety Agency. All rights reserved. 3 / 4 Proprietary document. Copies are not control led. Confirm revision status through the EASA

- Internet/Intranet. Table 2 : I nspection i ntervals (whichever occurs first
, FH or FC)

Aeroplane configuration AFT > 1,5 FH/FC AFT ≤ 1,5

FH/FC All aeroplane configurations ( interval counted from the date of the last inspection) 7 800 FH 3 600

FC 5 800

FH 3 900

FC

(2 ) For an aeroplane which, on the effective date of this AD, has exceeded the applicable threshold and/or interval as specified in Table 1 or Table 2 of this AD , as applicable to aeroplane configuration , the initial compliance time (or Grace Period) is 1 00 0 FC counted from the effective date of this AD. However
, this new compliance time must not exceed the compliance time as specified in Airbus SB A300

- 53

- 6122 at Revision 02

. ( 3 ) If, during any inspection as required by paragraph (1) of this AD, discrepanci es are detected, before next flight, accomplish the applicable corrective actions in accordance with the instructions of Airbus SB A300

- 53

- 6122 Revision 04

. ( 4 ) Corrective actions, as required by paragraph ( 3 ) of this AD, do not constitute terminating act ion for the repetitive inspections required by paragraph (1) of this AD. ( 5 ) Inspections and corrective actions
, accomplished before the effective date of this AD in accordance with the instructions of Airbus SB A300

- 53

- 6122 at original issue up to Revisi on 0 3
, are acceptable to comply with the initial requirements of paragraph s (1) and ( 3 ) of this AD. After the effective date of this AD, all repetitive inspections and corrective actions must be accomplished in accordance with the instructions of Airbus SB A300

- 53

- 6122 Revision 0 4

.

MODIFICATION : ( 6 ) Within the compliance time defined in Table 3 of this AD
, as applicable depending on AFT, reinforce the upper frame feet fittings in accordance with the instructions of Airbus SB A300

- 53

- 6 125 Revision 03.

Table 3: Compliance time for modification (whichever occurs first
, FH or FC )

AFT Compliance time ( since

aeroplane first flight ) Aeroplane s with AFT >1,5 FH/FC 18 200 FH or 8 400 FC
Aeroplane s with AFT ≤ 1,5 FH/FC 13 700 FH or 9 100 FC

( 7 ) For aeroplanes whic h
, before the effective date of this AD, have already been modified in production by Airbus modification 12168 or in

- service through Airbus SB A300

- 53

- 6125 ( at original issue up to Revision 02 ), not later than 6 months before reaching the action threshold defined in Table 4 of this AD, as applicable
, depending on AFT , contact Airbus for further instructions and accomplish those instructions accordingly.EASA AD No.: 2013

- 0295

TE.CAP.00110

- 00 3 © European Aviation Safety Agency. All rights reserved. 4 / 4 Proprietary document. Copies are not control led. Confirm revision status through the EASA

- Internet/Intranet. Table 4: Action t hreshold for aeroplanes modified prior to this AD (from the date of accomplishment of the modification in production or in service, as applicable)

AFT Compliance t ime
AFT > 1.5 FC 32 100 FC
AFT ≤ 1.5 FC 34 700 FC

( 8 ) For an aeroplane which, on the effective date of this AD, has exceeded the applicable compliance time as specified in Tab le 3 and/or the action threshold as specified in Table 4 of this AD , as applicable
, depending on AFT , the initial compliance time (or Grace Period) is 1 000 FC counted from the effective date of this AD. However
, this new compliance time must not exceed t he compliance time as specified in Airbus SB A300

- 53

- 612 5 at Revision 02

. ( 9 ) Modification of an aeroplane a s required by paragraph ( 6 ) or ( 7 ) of this AD do es not constitute terminating action for the repetitive inspections required by paragraph ( 1 ) of th is AD.

Ref. Public ations: Airbus S B A300

- 5 3

- 6 1 22 original issue dated 0 9 February 2000
, or Re vision 01 dated 05 September 2001
, or Revision 02 dated 17 June 2002
, or Revision 03 dated 25 August 2011 , or Revision 04 dated 27 February 2012

. Airbus SB A300

- 5 3

- 61 25 original issue dated 0 8 N ovember 2000
, or Revision 01 dated 25 February 2005
, or Revision 02 dated 13 September 2011
, or Revision 03 dated 13 September 2011

. The use of later approved revisions of these documents is acceptable for compliance with th e requirements of this AD.

Remarks: 1. If requested and appropriately substantiated, EASA can approve Alternative Methods of Compliance for this AD.
2. The original issue of this AD was posted on 01 October 2012 as PAD 12

- 124 for consultation until 29 October 2012. The Comment Response Document can be found at http://ad.easa.europa.eu

. 3. Enquiries regarding this A D should be referred to the Safety Information Section, Executive Directorate , EASA. E

- mail : ADs@easa.europa.eu

. 4. For any question concerning the technical content of the requirements in this AD, please contact: AIRBUS SAS

– EIAW (Airworthiness Office), E

- mail: continued.airworthiness

- wb.external@airbus.com

.