EASA AD No : 2011-0034

EASA Form 110 Page 1/2 

## EASA AIRWORTHINESS DIRECTIVE

AD No.: 2011-0034

Date: 02 March 2011

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 th e activities of EASA under Article 66 of that Regulation.
This AD is issued in accordance with EC 1702/2003, Part 21A.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 opera te 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) exemptio n]. 

### Type Approval Holder’s Name :

AIRBUS Type/Model designation(s) :
A319, A320 and A321 aeroplanes

TCDS Number : EASA.A.064

Foreign AD : Not applicable

Supersedure : None



### ATA 57 Wings – Outer Wing Refuelling Aperture Electrical Bonding – Inspection / Modification

Manufacturer(s): Airbus (formerly Airbus Industrie)

Applicability: Airbus A319-111, A319-112 , A319-132, A320-111, A320-211, A320-212, A320-214, A320-232, A321-111, A3 21-211, A321-212 and A321-231 aeroplanes, manufacturer serial numbers (MSN): 0039, 0078, 0109, 0118, 0120, 0153, 0174, 0187, 0203, 0215, 0218, 0226, 0227, 0228, 0236, 0237, 0269, 0270, 0278, 0285, 0286, 0287, 0288, 0294, 0301, 0337, 0377, 0462, 0463, 0464, 0465, 0520, 0523, 0528, 0876, 0888, 0921, 0935, 0974, 1014, 1102, 1130, 1160, 1162, 1177, 1215, 1250, 1287, 1336, 1388, 1404, 1444, 1449, 1476, 1505, 1524, 1564, 1605, 1616, 1622, 1640, 1645, 1658, 1677, 1691, 1729, and 1905.
Reason: Cases of corrosion findings have been reported on the overwing refuelling aperture (used to fill the fuel tank by gravity) on the wing top skin. The reported corrosion was on the mating surface of the aperture flange, underneath the refuel adaptor. Corrosion findings have been repaired on a case by case basis in accordance with approved data. For certain aeroplanes (id entified by MSN in the app licability section of this AD), the provided repair co ntained instructions to apply primer coating on the mating surface. Since doing those repairs , it has been found that this primer coating may prevent proper electrical bonding provision between the overwing refuelling cap adaptor and the wing skin. This condition, if not corrected, could, in combination with a lightning strike in this area, create a source of ignition in a fuel tank, possibly resulting in a fire or explosion and consequent loss of the aeroplane. For the reasons described above, this AD requires a one-time electricalEASA AD No : 2011-0034

EASA Form 110 Page 2/2 bonding check between the gravity fill re -fuel adaptor and the top skin panels on the affected aeroplanes and, in case of findings, the application of the associated corrective actions.

Effective Date: 16 March 2011

Required Action(s) and Compliance Time(s): Required as indicated, unless previously accomplished:
Within 24 months after the effective dat e of this AD, carry out an electrical bonding check between the gravity fill re -fuel adaptor and the top skin panels on both wings and, in case of discre pancies, before next flight, apply the associated corrective actions, all actions to be done in accordance with the instructions defined in Airbus Service Bulletin A320-57-1152.

Ref. Publications: Airbus Service Bulle tin A320-57-1152 at Original issue. The use of later approved revisions of this document 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 28 January 2011 as PAD 11-008 for consultation until 25 February 2011. No comments were received during the consultation period. 3. Enquiries regarding this AD should be referred to the Airworthiness Directives, Safety Management & Re search Section, Certification Directorate, EASA. E-mail ADs@easa.europa.eu

. 4. For any question concerning the tec hnical content of the requirements in this AD, please contact: AIRBUS – Airworthiness Office – EAS Fax +33 5 61 93 44 51, E-mail: account.airworth-eas@airbus.com

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