EASA AD No.: 2013

- 0184R1

TE. CAP.0011 0

- 003 © European Aviation Safety Agency. All rights reserved. 1 / 5 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. 

## EASA AIRWORTHINESS DIRECTIVE

AD No

. : 2013 - 0184 R1

Date: 22 August 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 requ irements of that AD, unless otherwise specified by the Agency [EC 2042/2003 Annex I, Part M.A.303] or agreed with the Authority of the State of Registry [EC 216/2008, Article 1 4(4) exemption]. 

### Design Approval Holder’s Name: AIRBUS Type/Model designation(s ): A300 and A300

- 600 aeroplanes

TCDS Number: France No. 145
F oreign AD: Non applicable Supersedure: This AD supersedes DGAC France AD F

- 2002

- 184 dated 0 3 April 2002.



### ATA 53 Fuselage
– Frame 47 Splice Fitting Holes Between S tringers 24

and 26
– Inspection
Manufacturer(s): Airbus (formerly Airbus Industrie) Applicability: Airbus A300 B4

- 103, A300B4

- 120, A300B4

- 203, A300B4

- 2C, A300C4

- 203 and A300F4

- 203 all Manufacturer Serial Numbers (MSN) and Airbus A300

- 600 , all certified models , all MSN.
Reason: In order t o prevent crack development in the fastener holes at F rame (FR) 47 splicing joint on A300 aeroplanes, Airbus develop ed modification (Mod) 5890 for aeroplanes i n production and issued corresponding S ervice Bulletin (SB) A300

- 53

- 0199 for aeroplanes in service

. Subsequently, c racks were found on F R 47 splice fitting between stringers (STRG) 24 and 26 on A300 ae r o plane s previously modified by SB A300

- 53

- 0199. This condition, if not detected and corrected, could reduce the structural int egrity of the aeroplane. To address this potential unsafe condition, DGAC France issued AD 2002

- 184 , superseding AD 85

- 152

- 069 and AD 1999

- 515

- 298 , to require repetitive High Frequency Eddy Current ( HFEC ) rotating probe inspection s of the splice fitting between STRG 2 4 and 26 and , depending on findings, corrective action (s). DGAC France AD 2002

- 184(B) ex pa nd ed the applicability to A30 0

- 600 aeroplane s , which have the same design. Since that AD was issued, a fleet survey and updated Fatigue and Damage Tolerance analyses have been performed in order to substantiate the second A300

- 600 Extended Service Goal (ESG2) exercise. The results of these analyses have determined that the inspection threshold and interval s forEASA AD No.: 2013

- 0184R1

TE. CAP.0011 0

- 003 © European Aviation Safety Agency. All rights reserved. 2 / 5 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. A300

- 600 aeroplanes must be reduced to allow timely detection of these cracks and the accomplishment of an applicable corrective action. For the reasons described above, AD 2013

- 0184 retains the requirements of DGAC France AD 2002

- 184 , which is superseded, but requires accomplishment of the actions for A300

- 600 aeroplanes within the new thresholds and intervals introduced with Revision 05 of Airbus SB A300

- 53

- 6123. This AD was revised to correct the splice s Part Numbers (P/N) in Table 4 of Appendix 1 of this AD. Also, r eference is now made to Airbus SB A300

- 53

- 6123 Revision 06, which corrected this mistake compared to Revision 05.

Effective Date: Revision 1: 05 September 2013 Original issue: 27 August 2013 Required A ction(s) and Compliance Time(s) : Required as indicated, unless accomplished previously: (1) Within the applicable thre shold s as defined in Appendix 1, T able 1 or Table 2 , of this AD , and , thereafter , at interval s not to exceed the applicable value s as defined in Appendix 2 , Table 3 or Ta ble 4 , of this AD, as applicable, remove the fasteners and accomplish an HFEC rotating probe inspection of the splice fitting between STRG 24 and 26 in accordance with the instruction s of Airbus SB A300

- 53

- 6123 Revision 06 , or SB A300

- 53

- 0350 Revision 03 , as applicable to aeroplane model. Before release to service of the aeroplane a fter each HFEC inspection, provided no cracks are found , install new fasteners. (2) If , during any inspection as required by paragraph (1) of this AD , cracks are found, before next flight, accomplish the applicable corrective actions in accor dance with the instructions of A irbus SB A300

- 53

- 6123 Revision 06 , or SB A300

- 53

- 0350 Revision 03 , as applicable to aeroplane model. (3) Inspections and corrective actions, accomplished before the effective date of this AD in accordance with the instructions of Airbus SB A300

- 53

- 6123 at original issue up to Revision 05 , or SB A300

- 53

- 0350 at original issue up to Revision 02, as applicable , are acceptable to comply with the requirements of paragraph s (1) and (2) of this AD . A fter the effective date of this AD, the repetitive inspections required by paragraph (1) and the corrective actions required by paragraph (2) of this AD must be accomplis hed in accordance with the instructions of Airbus SB A300

- 53

- 6123 Revision 06 , or SB A300

- 53

- 0350 Revision 03 , as a pplicable to aeroplane model.
Ref. Public ations: Airbus SB A300

- 53

- 0199 original issue dated 08 July 1985, or Revision 01 dated 28 November 1985, or Revision 02 dated 06 February 1987, or Revision 03 dated 03 June 1987, or Revision 04 dated 12 November 2002

. Airbus SB A300

- 53

- 0350 original issue dated 25 October 1999 , or Revision 01 dated 18 December 2001 , or Revision 02 dated 12 November 2002 , or Revision 03 dated 26 July 2007

. Airbus SB A300

- 53

- 6123 original issue dated 25 October 1999 , or Revision 02 dated 12 November 2002, or Revision 03 dated 20 August 2004, or Revision 04 dated 25 April 2008, or Revision 05 dated 01 August 2011 , or Revision 06 dated 28 September 201 1

. Airbus SB A300

- 53

- 6131 original issue dated 22 August 2001

. The use of later approved revisions of th e s e document s is acceptable for compliance with the requirements of this AD.
Remarks: 1. If requested and appropriately substantiated, EASA can approve Alternative Methods of Compliance for this AD.EASA AD No.: 2013

- 0184R1

TE. CAP.0011 0

- 003 © European Aviation Safety Agency. All rights reserved. 3 / 5 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. 2. This AD was posted on 12 March 2013 as PAD 13

- 045 for consultation until 09 April 2013

. The Comment Response Document can be found at http://ad.easa.europa.eu

. 3. Enquiries regard ing this AD 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

– E I AW (Airworthiness Office), Email: continued.airworthiness

- wb.external@airbus.comEASA AD No.: 2013

- 0184R1

TE. CAP.0011 0

- 003 © European Aviation Safety Agency. All rights reserved. 4 / 5 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. 

### Appendix 1

– Inspection Thresholds

Table 1: Inspection t hresholds for A300 aeroplanes , w hichever occurs later, A or B Affected Aeroplanes: (pre

- or post
- Mod 5890, or pre - or post
- SB A300

- 53

- 0199) Compliance Time A : whichever occurs first since aeroplane first flight
A300B4 - 100 aeroplanes A300B4 - 200 , A300C4 - 203 and A300F4 - 203 aeroplanes
Pre

- Mod /

- SB 4 0 00 f light cycles (FC) or 8 0 00 f light hours (FH ) 3 300 FC or 6 8 00 FH

Post

- Mod /

- SB 10 500 FC or 21 2 00 FH 8 650 FC or 1 8 000 FH Compliance time B: For all A300B4 models post

- Mod 5890 , or post
- SB A300

- 53

- 0199 : Before exceeding 750 FC or 1 500 FH , whichever occurs first after 13 April 2002 ( the ef fective date of DGAC France AD 2002

- 184). For all other A300 models: Before exceeding 1 800 FC or 3 000 FH, whichever occurs first after 13 April 2002 ( the effective date of DGAC France AD 2002

- 184)

.

T able 2: Inspection t hresholds for A300

- 600 aeroplanes , w hichever occurs later, A or B Affected Aeroplanes: (pre

- or post
- Mod 58 90, or pre - or post
- SB A300

- 53

- 6 1 31 ) Compliance Time A : whichever occurs first since aeroplane first flight Average flight Time (AFT) more than 1,5 hours AFT equal to or less than 1,5 hours
Pre

- Mod /

- SB 2 500 F C or 5 500 FH 2 700 FC or 4 100 FH
Post

- Mod /SB 6 800 FC or 14 700 FH 7 300 FC or 11 000 FH Compliance time B: 800 FC or 1 750 FH , whichever occurs first after the effective date of this AD.EASA AD No.: 2013

- 0184R1

TE. CAP.0011 0

- 003 © European Aviation Safety Agency. All rights reserved. 5 / 5 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. 

### Appendix 2

– Inspection Intervals

Table 3: I nspection i ntervals for A300 aeroplanes , w hichever occurs later, A or B Affected Aeroplanes: (pre

- or post
- Mod 5890, or pre - or post
- SB A300

- 53

- 0199 ; splice P/N installed ) Compliance Time A : whichever occurs first
A300B4 - 100 aeroplanes A300B4 - 200, A300C4 - 203 and A300F4 - 203 aeroplanes
Pre

- Mod /

- SB 2 8 00 FC or 5 7 00 FH 2 3 00 FC or 4 8 00 FH Post

- Mod /

- SB ; P/N A53834139

- 200 /

- 201
Post

- Mod /

- SB ; P/N A53834139

- 202 /

- 203 , or P/N A53812635

- 200 /

- 201 4 8 00 FC or 9 7 00 FH 3 95 0 FC or 8 2 00 FH Compliance time B: For all A300B4 models post

- Mod 5890 , or post
- SB A300

- 53

- 0199 : Before exceeding 750 FC or 1 500 FH , whichever occurs first after 13 April 2002 ( the ef fective date of DGAC France AD 2002

- 184). For all other A300 models: Before exceeding 1 800 FC or 3 000 FH, whichever occurs first after 13 April 2002 ( the effective date of DGAC France AD 2002

- 184)

.

Table 4: I nspection i ntervals for A300

- 600 aeroplanes , w hichever occurs later, A or B Affected Aeroplanes: (pre

- or post
- Mod 5890, or pre - or post
- SB A300

- 53

- 6 1 31 ; splice P/N installed) Compliance Time A : whichever occurs first AFT more than 1,5 hours AFT equal to or less than 1,5 hours
Pre

- Mod /

- SB 2 000 FC or 4 300 FH 2 100 FC or 3 200 FH Post

- Mod /

- SB ; P/N A53834139

- 202 /

- 203
Post

- Mod /

- SB ; P/N A53812635

- 200 /

- 201 /

- 202 /

- 203 1 600 FC or 3 500 FH 1 700 FC or 2 600 FH Compliance time B: 800 FC or 1 750 FH , whichever occurs first after the effective date of this AD.