EASA AD No.: 20 14

- 0 197

TE. CAP.0011 0

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

- Internet/Intranet. 

## EASA AIRWORTHINESS DIRECTIVE

AD No

. : 20 14 - 0 197

Date: 04 September 2014
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 accordan ce 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 ope rate an aircraft to which an AD applies, except in accordance with the requirements 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 14(4) exemption]

. 

### Design Approval Holder’s Name: AIRBUS Type/Model designation(s): A330

- 200F aeroplanes

TCDS Number: EASA.A.004
F oreign AD: Not applicable Supersedure: None



### ATA 53 Fuselage

– Frame / Stringer Attachment s – Inspection / Repair

Manufacturer(s): Airbus Applicability: Airbus A330

- 223F and A330

- 243F aeroplanes, m anufacturer serial numbers 1004, 1032, 1051, 1062, 1070, 1092, 1115, 1136, 1148, 1164, 1175, 1180, 1320, 1332, 1344, 1350, 1368, 1380, 1386, 1406, 1414, 1418 and 1428.
Reason: During inspection of various fuselage areas on s om e A330

- 200F aeroplanes on the production line, prior to delivery, some fasteners were found missing. This condition, if not detected and corrected, could lead to crack initiation and propagation, possibly resulting in reduced structural integrity of the fuselage. To address thi s condition, Airbus issued several Service Bulletins (SB), providing inspection and modification instructions, as applicable

. For the reasons described above, this AD requires detailed inspections of the affected areas and, depending on findings, accomplishment of the applicable corrective actions.

Effective Date: 18 September 2014 Required A ction(s) and Compliance Time(s) : Required as indicated, unless accomplished previously: (1) Within 72 months after aeroplane first flight , a ccomplish a detailed inspection (DET) of all fuselage zones as specified in Appendix 1 of this AD, Tables 1, 2 and 3, as applicable, in accordance with the instructions of Airbus Inspection SB A330

- 53

- 3202, SB A330

- 53

- 3212, SB A330

- 53

- 3213 , and SB A330

- 53

- 3214

.EASA AD No.: 20 14

- 0 197

TE. CAP.0011 0

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

- Internet/Intranet. (2) If, during the DET as required by paragraph (1) of this AD, for the fuselage zones in Appendix 1, Tables 1, 2 and 3 of this AD, any discrepancy is detected , before next flight, accomplish a DET of the adjacent fastener rows in accordance with the instructions of Airbus Inspection SB A330

- 53

- 3202, SB A330

- 53

- 3212, SB A330

- 53

- 3213 , and SB A330

- 53

- 3214, as applicable

. (3) If, during the DET as required by paragraph (2) of this AD, for the fuselage zones in Appendix 1, Tables 1, 2 and 3 of this AD, no discrepancy is detected, before next flight, modify the affected fuselage zone of the aeroplane (installation of correct fasteners) in accordance with the instructions of Airbus Modification SB A330

- 53

- 3216 , or SB A330

- 53

- 321 7, or SB A330

- 53

- 321 8, or SB A330

- 53

- 321 9 , as applicable. (4) If, during the DET as required by paragraph (2) of this AD, for the fuselage zones in Appendix 1, Tables 1, 2 and 3 of this AD, any discrepancy is detected as identified in Airbus Inspection SB A330

- 53

- 3202, SB A330

- 53

- 3212, SB A330

- 53

- 3213 , or SB A330

- 53

- 3214, as applicable , before next flight, contact Airbus for approved repair instructions (Repair Design Approval Sheet

– RDAS) and accomplish those instructions accordingly

. Ref. Public ations: Airbus Inspection SB : Airbus SB A330

- 53

- 3202 original issue , dated 06 May 2014. Airbus SB A330

- 53

- 3212 original issue , dated 06 May 2014. Airbus SB A330

- 53

- 3213 original issue , dated 06 May 2014. Airbus SB A330

- 53

- 3214 original issue , dated 06 May 2014. Airbus Modification SB : Airbus SB A330

- 53

- 3216 original issue , dated 06 May 2014. Airbus SB A330

- 53

- 3217 original issue , dated 06 May 2014. Airbus SB A330

- 53

- 3218 original issue , dated 06 May 2014. Airbus SB A330

- 53

- 3219 original issue , dated 06 May 2014. The use of later approved revisions of these documents 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

. 2. This AD was posted on 08 July 2014 as PAD 14

- 115 for consultation until 05 August 2014

. No comments were received during the consultation

. 3. Enquiries regarding this AD should be referred to the Safety Information Section, Certification Directorate, EASA. E

- mail: ADs@easa.europa.eu

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

– Airworthiness Office

– EIAL; E

- mail: airworthiness.A330

- A340@airbus.com

.EASA AD No.: 20 14

- 0 197

TE. CAP.0011 0

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

- Internet/Intranet.



### A ppe n di x 1

– Fuselage areas to be i nspected and modified, as applicable

Table 1 Fuselage zone identification Applicable Airbus Inspection SB Applicable Airbus

Modification SB Frame Stringer Left Hand (LH) Side Right Hand

(RH) Side 21

- 22 X X A330

- 53

- 3202 A330

- 53

- 3216 26/28 26 X 35 24

- 25 X 57 26 X X
A330

- 53

- 3212 A330

- 53

- 3217 58A 29

- 30 X 58A 31

- 32

- 33 X 59 23

- 24

- 25 X 59A 45

- 46

- 47 X

A330

- 53

- 3213 A330

- 53

- 3218 60A 26 X 64 24 X 65

- 66 37 X 66 27 X 68 29

- 30 X
A330

- 53

- 3214 A330

- 53

- 3219 69 33 X 71 14 X 72 5 X X

Table 2 Fuselage zone identification Applicable Airbus Inspection SB Applicable Airbus

Modification SB Frame Stringer Left Hand (LH) Side Right Hand

(RH) Side 19 52

- 53 X A330

- 53

- 3202 A330

- 53

- 3216 30 33

- 34 X 30 to 37

- 37.1

- 37.3

- 37.4 41

- 42 X 58

- 59 38 X
A330

- 53

- 3212 A330

- 53

- 3217 58 41 X X 59 26 X 59 40 X 59 15 X
A330

- 53

- 3213 A330

- 53

- 3218 61 14

- 15 X 65 22A

- 23

- 25 X 65

- 66 45

- 46 X 72 26

- 27 X
A330

- 53

- 3214 A330

- 53

- 3219 72 30 X 72 43 X 72 46

- 47 XEASA AD No.: 20 14

- 0 197

TE. CAP.0011 0

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

- Internet/Intranet. 

### Appendix 1 (continued)

– Fuselage a reas to be inspected and modified, as applicable

Table 3 Fuselage zone identification Applicable Airbus Inspection SB Applicable Airbus

Modification SB Frame Stringer Left Hand (LH) Side Right Hand

(RH) Side 20 43 X A330

- 53

- 3202 A330

- 53

- 3216 37.3 44 X