EASA AD No : 2011-0084 

EASA Form 110 Page 1/2 

EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2011-0084 

Date: 24 May 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) : 

A300, A300-600 and A300-600ST aeroplanes 

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

Foreign AD : Not Applicable 

Supersedure : None 

ATA 24 Electrical Power – Fire Shut-Off Valve (FSOV) Bonding Lead and 

Wiring – Inspection / Repair 

Manufacturer(s): AIRBUS (formerly AIRBUS INDUSTRIE). 

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

and Airbus A300F4-608ST aeroplanes, all serial numbers. 

Reason: During a scheduled maintenance check, one operator reported inoperative 

FSOV. Investigations showed damage at wire located between engine 2 

Hydraulic FSOV and wing rear spar, in the zones 575/675, and at bonding 

lead, located between wing Rib 7A and Rib 8 below Hydraulic Pressure 

Lines. 

Similar Inspections on different aeroplanes have shown that one of the 

causes of damage, is the contact between bonding lead and the harness, 

due to over length of the bonding lead. 

As the affected wire is not powered during normal operation, no defect had 

been detected. The defect was detected when a test was performed on the 

FSOV during maintenance check by the operator. 

This condition, in the scope of published FAA SFAR88 and JAA Internal 

Policy INT/POL/25/12, is considered to be a potential source of sparks in the 

wing trailing edge area and if not detected, could lead to an uncontrolled 

engine fire. 

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

wires located between LH/RH engines Hydraulic FSOV and wing rear spar in 

the zones 575/675, and the bonding lead that is located between Rib 7A and 

Rib 8 below Hydraulic Pressure Lines, and corrective actions depending on 

findings. 

Effective Date: 07 June 2011 
EASA AD No : 2011-0084 

EASA Form 110 Page 2/2 

Required Action(s) 

and Compliance 

Time(s): 

Required as indicated, unless already accomplished: 

(1) Within 30 months or 4 500 flight hours, whichever occurs first after the 

effective date of this AD, do a one-time detailed inspection of the FSOV 

bonding leads and of the wires located on wing rear spar at LH and RH 

side, in accordance with the accomplishment instructions of Airbus 

Service Bulletin (SB) A300-24-0106 or SB A300-24-6108 or SB A300-

24-9016, as applicable to aeroplane model. 

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

length of the bonding lead(s) is more than 80 mm (3.15 in), before next 

flight, replace the bonding lead(s) with a new bonding lead having a 

length equal to 80 mm (3.15 in), in accordance with the accomplishment 

instructions of SB A300-24-0106 or SB A300-24-6108 or SB A300-24-

9016, as applicable to aeroplane model. 

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

contact(s) and/or chafing(s) is/are found, before next flight, repair the 

wire(s) in accordance with the accomplishment instructions of SB A300-

24-0106 or SB A300-24-6108 or SB A300-24-9016, as applicable to 

aeroplane model. No further action is required after repair. 

(4) From the effective date of this AD, do not install any bonding lead with 

length more than 80 mm, located between LH/RH engine Hydraulic 

FSOV and wing rear spar in the zones 575/675, unless in compliance 

with the requirements of this AD. 

Ref. Publications: AIRBUS Service Bulletin A300-24-0106 original issue, 

AIRBUS Service Bulletin A300-24-6108 original issue and 

AIRBUS Service Bulletin A300-24-9016 original issue, 

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 31 January 2011 as PAD 11-009 for consultation 

until 28 February 2011. The Comment Response Documents can be 

found at http://ad.easa.europa.eu/. 

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 SAS – EAW (Airworthiness Office, 

Telephone: + 33 5 61 18 41 39, Fax:+ 33 5 61 93 44 51).