EASA AD No.: 2013-0193

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EASA AIRWORTHINESS DIRECTIVE

AD No.: 2013-0193

Date: 23 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 

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 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].

Design Approval Holder’s Name:

AIRBUS

Type/Model designation(s):

A300, A300-600 and A300-600ST

aeroplanes

TCDS Numbers: France No. 145 and EASA.A.014

Foreign AD: Not applicable

Supersedure: None

ATA 28 Fuel – Outer Tank Sensor Harness – Inspection / Modification

Manufacturer(s): Airbus (formerly Airbus Industrie)

Applicability: Airbus A300, A300-600 and A300-600ST aeroplanes, all certified models, all 

manufacturer serial numbers.

Reason: During a scheduled maintenance check on an A300 aeroplane, chafing was 

found on the surge tank overflow sensor harness. The harness was found to 

contact the Magnetic Fuel Level Indicator (MFLI) canister.

Prompted by these findings, DGAC France issued AD 1999-404-293 to require

modification of the harness routing in accordance with the instructions of Airbus 

SB A300-28-0058 or SB A300-28-6020, as applicable to aeroplane model.

Since that AD was issued, maintenance work on modified A300-600 

aeroplanes revealed some chafing of the harness, creating a potential contact 

between the electrical wire and fuel tank structure. Investigations have shown 

that although measures were taken to prevent contact of the harness with the 

MFLI (through modification 04489), the installation can be subject to human 

error. As the MFLI is integral to the access panel in this location, any potential 

contact with the harness (as a result of incorrect installation) is hidden.

This condition, if not detected and corrected, could lead to electrical arcing, 

possibly resulting in a fuel tank explosion and loss of the aeroplane. To address 

this potential unsafe condition, Airbus issued SB A300-28-0091 for A300 

aeroplanes, SB A300-28-6109 for A300-600 aeroplanes and A300-28-9022 for 

A300-600ST aeroplanes.

For the reasons described above, this AD requires a one-time inspection of the 

harness and, depending on findings, corrective actions, as well as replacement 

of angle brackets by error-proof harness brackets.
EASA AD No.: 2013-0193

TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved. 2/2

Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.

Effective Date: 06 September 2013

Required Action(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 

visual inspection of the outer tank sensor harness between ribs 26 and 27 

in accordance with the instructions of Airbus SB A300-28-0091, SB A300-

28-6109 or SB A300-28-9022, as applicable to aeroplane model.

(2) If, during the inspection as required by paragraph (1) of this AD, any 

previous repairs are identified or braid and wire insulation is found 

damaged with conductor exposed, before next flight, contact Airbus for

approved repair instructions and, within the compliance time defined in 

those instructions, accomplish the repair accordingly.

(3) If, during the inspection as required by paragraph (1) of this AD, braid and 

wire insulation is found damaged without conductor exposed, before next 

flight, accomplish the applicable corrective actions in accordance with the 

instructions of Airbus SB A300-28-0091, SB A300-28-6109 or SB A300-28-

9022, as applicable to aeroplane model.

(4) Concurrent with the inspection as required by paragraph (1) of this AD,

provided that no damage was found, or before next flight after the 

accomplishment of corrective actions as required by paragraph (2) or (3) of 

this AD, as applicable, install modified and error–proof angle brackets 

attached to stringer 15 between ribs 26 and 27 in accordance with the 

instructions of Airbus SB A300-28-0091, SB A300-28-6109 or SB A300-28-

9022, as applicable to aeroplane model.

Ref. Publications: Airbus SB A300-28-0091 original issue dated 05 March 2013.

Airbus SB A300-28-6109 original issue dated 05 March 2013.

Airbus SB A300-28-9022 original issue dated 20 March 2013.

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 25 July 2013 as PAD 13-106 for consultation until 

22 August 2013. No comments were received during the consultation 

period.

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 content of the requirements in 

this AD, please contact:

AIRBUS SAS – EIAW (Airworthiness Office)

Email: continued.airworthiness-wb.external@airbus.com