EASA AD No.: 2013

- 0188

TE. CAP.0011 0

- 00 3 © European Aviation Safety Agency. All rights reserved. 1 / 2 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. 

## EASA AIRWORTHINESS DIRECTIVE

AD No

. : 2013

- 0188

Date: 19 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 Eu ropean 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 a n 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 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) exemption]. 

### Design Approval Holder’s Name:
AIRBUS Type/Model designation(s): A310 aeroplanes

TCDS Number: France No. 145

F oreign AD: Not applicable

Supersed ure: None



### ATA 28 Fuel

– F uel Q uantity I ndicator P robes

– Inspe ction / Modification

Manufacturer(s): Airbus ( formerly Airbus Industrie)

Applicability: Airbus A310

- 304, A310

- 308, A310

- 322, A310

- 324 and A310

- 325 aeroplan es , all manufacturer serial numb ers on which Airbus Modification (M od.) no

. 12248 has been embodied

.
Reason: Airbus investigations on A300 aeroplanes revealed insufficient clearance between the Fuel Quantity Indicator ( FQI ) probes and adjacent structu re or metallic components in the win g fuel tanks. A300

- 600 and A310 aeroplanes are also affected as they are identical in design. This condition, if not detected and corrected, could lead to electric arcing in a fuel tank in case of li ghtning strike, which could result in ignition and conseq uent fire or explosion in the fuel tank

. To address this potential unsafe condition, Airbus issued Service Bulletin (SB) A300

- 28

- 0080, SB A300

- 28

- 6065 and SB A310

- 28

- 2145 and DGAC France issued AD 2000

- 455

- 322 to cover A300 aeroplanes and AD 2002

- 170 to co ver A300

- 600 and A310 aeroplanes (both ADs were later revised )

. Since those ADs were issued, further analysis showed that they do not cover all potentially affected aeroplanes : A310 aeroplanes with optional M od. no. 12248 embodied were excluded from the a pplicability of DGAC France AD 2002

- 170(B), but are potentially affected, and therefore addressed through this AD.
For the reason s described above, this AD require s a one
- time inspection of the affected aeroplanes for sufficient clearance between FQI probe s and adjacent structure / metallic parts and, depending on findings , modification of the FQI probes.

Effective Date: 02 September 2013EASA AD No.: 2013

- 0188

TE. CAP.0011 0

- 00 3 © European Aviation Safety Agency. All rights reserved. 2 / 2 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. Required A ction(s) and Compliance Time(s) : Required as indicated, unless accomplished previously: (1) Within 30 months after the effective date of this AD, accomplish a one
- time inspection of the clearance between the FQI probes, located in the Trimmable Horizontal Stabilizer tank, and adjacent structure or metallic components in accordance with the instructions of Airbus SB A310

- 28

- 2145

. (2) If, during the inspection as required by paragraph (1) of this AD, the clearance of an FQI probe is f ound to be below the minimum allowed, before next flight

, modify each affected FQI probe in accordance with the instructions of Airbu s SB A310

- 28

- 2145

.

Ref. Public ations: Airbus SB A310

- 28

- 2145 origi n al issue dated 21 August 2001, or Revision 01 dated 04 March 2003.
The u se of later approved revisions of this document is acceptable for compliance with the requirements of this AD.

Rema rks: 1. If requested and appropriately substantiated, EASA can approve Alternative Methods of Compliance for this AD.

2. This AD was posted on 17 July 2013 as PAD 13

- 099 for consultation until 14 August 2013. No comments were received during the consultation per iod.

3. Enquiries regarding 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 conte nt of the requirements in this AD, please contact: AIRBUS SAS

– EIAW (Airworthiness Office )

, Email: continued.airworthiness

- wb.external@airbus.com

.