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Airbus 306/310, Electrical Power, Wing Electrical Installation Modification, EASA AD 2019-0014

Reference:

https://ad.easa.europa.eu/ad/2019-0014

Applicability:

Following Aeroplane types, all certified models, all manufacturer serial numbers:

  • Airbus A300-600,
  • A300-600ST, and
  • A310

Reason:

Following publication of Federal Aviation Administration SFAR 88 (Special Federal Aviation Regulation 88), EASA issued AD 2006-0076 requiring inspection and corrective action to improve the explosion risk protection system for the left hand (LH) and right hand (RH) wings on A300, A300-600, A300-600ST and A310 aeroplanes. For A300-600, A300-600ST and A310 aeroplanes, the required detailed visual inspections of electrical bundles located in the leading and trailing edges of the RH and LH wings and a review of the wing electrical installation on the final assembly line have shown that the wing electrical installation does not comply with the minimum distance inspection criteria to the surrounding structure in a few wing locations.

This condition, if not detected and corrected, could lead to damage on the electrical harnesses and on the surrounding structure.

To address this unsafe condition, Airbus developed an improvement of the wing electrical installation to prevent possible chafing and subsequent damage to the electrical harnesses and surrounding structure. Consequently, EASA issued AD 2014-0034 to require installation of new bracket assemblies to ensure the clearance between the wiring and the structure, and installation of protective split sleeves as mechanical protection to the electrical harnesses.

After EASA AD 2014-0034 was issued, during embodiment of Airbus SB A300-24-6103 Revision 02 on an aeroplane, an installation problem was identified, which prompted Airbus to revise SB A300- 24-9014 Revision 01, and SB A300-24-6103 Revision 02. In addition, SB Information Transmission (SBIT) 14-0044 Revision 01 was issued to recommend to postpone embodiment of these two SBs, and to wait for the availability of Airbus SB A300-24-9014 Revision 02 and SB A300-24-6103 Revision 03. Subsequently, EASA issued AD 2015-0176, retaining the requirements of EASA AD 2014-0034, which was superseded, and requiring in addition, for A300-600 and A300-600ST aeroplanes only, installation of new bracket assemblies in shroud box (LH and RH side) to ensure adequate clearance between wirings and flap track carriage (LH and RH side).

After EASA AD 2015-0176 was issued, some operators reported that Airbus SB A300-24-6103 Revision 03 could not been implemented, due to missing installation information. Airbus supported the affected operators by providing the necessary installation information, and issued Airbus SB A300-24-6103 at Revision 04 to provide adequate installation information. Consequently, EASA issued AD 2016-0172, retaining the requirement of EASA AD 2015-0176, which was superseded, and requiring additional work for certain A300-600 aeroplanes.

Since EASA AD 2016-0172 was issued, Airbus SB A300-24-6103 Revision 05 was issued to include two sets of additional work which were not clearly defined in Revision 04:

  • Additional Work identified as A1 in the applicable SB is related to the installation of spacers to the guide Assembly for Group 1 and Group 3 aeroplanes (these spacers were removed at SB A300-24-6103 Revision 03).
  • Additional Work identified as A2 in the applicable SB is related to the modification of the Clamp on the routing on Rib 1 on the passage way to the shroud box LH and RH sides, for Group 3 aeroplanes. SB A300-24-6103 Revision 04 instructed operators to contact Airbus for the clamps installation, and Revision 05 describes this additional work.

For the reason described above, this AD retains the requirements of the EASA AD 2016-0172, which is superseded, and requires implementation of additional work on certain A300-600 aeroplanes.

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