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 the 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 operate 

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]. 

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, A321-211, 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 (identified by MSN in the applicability section of this 

AD), the provided repair contained 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 electrical 
EASA 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 date 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 discrepancies, 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 Bulletin 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 & Research Section, Certification 

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 – Airworthiness Office – EAS Fax +33 5 

61 93 44 51, E-mail: account.airworth-eas@airbus.com.