EASA AD No : 2010-0085 

EASA Form 110 Page 1/3 

EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2010-0085

Date: 03 May 2010

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) :

A310, A300-600 and A300-600ST aeroplanes

TCDS Number : France N° 145 and EASA.A.014 

Foreign AD : Not applicable 

Supersedure : This AD supersedes EASA AD 2010-0010 dated 21 January 2010. 

ATA 54 Nacelles / Pylons – Fuel Drain Pipe and Attachment Screws – 

Inspection / Replacement

Manufacturer(s): Airbus (formerly Airbus Industrie) 

Applicability: A310, A300-600 aeroplanes, all certified models, all serial numbers; and 

A300F4-608ST aeroplanes, all serial numbers. 

Reason: 

An operator of an A300-600 aeroplane reported finding a cracked pylon fuel 

drain pipe on engine #1.The pipe, Part Number (P/N) A71715020, had 

separated and the end was found 5.5 inches from the pylon aft bulkhead. A 

similar case was also reported on an A300F4-608ST aeroplane. 

The affected pylon fuel drain pipe runs from the top of the pylon primary 

structure to the aft part of the pylon rear secondary structure and is partly 

attached under the pylon lower spar. The pipe drains the double wall of the 

wing-to-pylon junction in the event of fuel leakage. 

After investigation, it was concluded that the damage of the pylon fuel drain 

pipe had been caused by chafing of the pipe against over-length screws that 

had been installed in accordance with the Illustrated Parts Catalogue (IPC) 

during a maintenance phase of the Lower Aft Pylon Fairing (LAPF). 

This condition, if not detected and corrected, could, in combination with fuel 

leakage in the pylon, lead to an accumulation of fuel in the lowest point of the 

LAPF. As high temperatures are present within the LAPF, and without 

ventilation, this could result in fuel (vapour) ignition and consequent fire. 
EASA AD No : 2010-0085 

EASA Form 110 Page 2/3 

To address and correct this unsafe condition, EASA issued AD 2010-0010, 

which required an inspection of the pylon fuel drain pipe and the attachment 

screws and, depending on findings, the necessary corrective actions. In case 

over-length screws are found to be installed, depending on location and 

aeroplane configuration, these must be replaced. 

After AD 2010-0010 was issued, Airbus found that the operational test, as 

included in the original ASB as part of the standard practice instructions, was 

insufficient to detect certain discrepancies. For this reason, a new operational 

test of the pylon fuel drain pipe has been defined, which has been introduced in 

Revision 01 of Airbus Alert Service Bulletin (ASB) A310-54A2040, A300-

54A6039 and A300-54A9004. 

For the reason described above, this new AD retains the requirements of EASA 

AD 2010-0010, which is superseded, and introduces a new compliance time for 

accomplishing the new operational test.

Effective Date: 17 May 2010 

Required Action(s) 

and Compliance 

Time(s): 

Required as indicated, unless already accomplished: 

(1) Within 1 month after the effective date of this AD, visually inspect the fuel 

drain pipes of the LAPF and check the length and P/N of the drain pipe 

attachment screws on the LAPF on the LH and RH pylons in accordance 

with the instructions of Airbus Alert Service Bulletin (ASB) A310-54A2040 

Revision 01, A300-54A6039 Revision 01 or A300-54A9004 Revision 01, as 

applicable to aeroplane model. 

(2) If discrepancies are detected during any inspection as required by 

paragraph (1) of this AD, before next flight, replace or repair the drain pipe 

in accordance with the instructions of Airbus ASB A310-54A2040, A300-

54A6039 or A300-54A9004, as applicable to aeroplane model. 

(3) If over-length screws are found to be installed, before next flight, remove 

these screws and replace them by screws with P/N NAS1102E3-10, 

NAS1102E3-12 or NAS560HK3-2, as applicable to location and aeroplane 

(engine) configuration, in accordance with the instructions of Airbus ASB 

A310-54A2040 Revision 01, A300-54A6039 Revision 01 or A300-54A9004 

Revision 01, as applicable to aeroplane model. 

(4) After the effective date of this AD, do not install screws on the LAPF, 

except those with P/N NAS1102E3-10, NAS1102E3-12 or NAS560HK3-2, 

as applicable to location and aeroplane (engine) configuration, in 

accordance with the instructions of Airbus ASB A310-54A2040 Revision 

01, A300-54A6039 Revision 01 or A300-54A9004 Revision 01, as 

applicable to aeroplane model. 

(5) Fuel drain pipes of the LAPF which have already been inspected, replaced 

or repaired before the effective date of this AD, in accordance with ASB 

A310-54A2040 original issue, A300-54A6039 original issue and A300-

54A9004 original issue, are considered compliant with the requirements of 

this AD. 

Note: Airbus documentation (IPC) has been updated to introduce the correct 

LAPF screws P/N and length reference for A310 and A300-600 and it will be 

done also for A300-600ST. 

Ref. Publications: 

Airbus ASB A310-54A2040 Revision 01, 

Airbus ASB A300-54A6039 Revision 01 and 

Airbus ASB A300-54A9004 Revision 01. 

The use of later approved revisions of these documents is acceptable for 
EASA AD No : 2010-0085 

EASA Form 110 Page 3/3 

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. The required actions and the risk allowance have granted the issuance of a 

Final AD with Request for Comments, postponing the public consultation 

process after publication. 

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 93 36 96, Fax: + 33 5 61 93 44 51).