EASA AD No : 2010-0175 

EASA Form 110 Page 1/3 

EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2010-0175 

Date: 18 August 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 No 145 and EASA A.014 

Foreign AD : Not applicable 

Supersedure : This AD supersedes EASA AD 2008-0055, dated 05 March 2008 

ATA 28 Fuel – Fuel Level Sensor Amplifier (FLSA) and Multi Tank Indicator 

(MTI) Wiring – Replacement 

Manufacturer(s): Airbus (formerly Airbus Industrie)

Applicability: Airbus A310 aeroplanes, all certified models, all manufacturer serial numbers 

(MSN); 

Airbus A300-600 aeroplanes, all certified models, all MSN; and 

Airbus A300F4-608ST aeroplanes, all MSN

Reason: One operator experienced failures of four Fuel Level Sensor-Amplifier (FLSA) 

and Multi Tank Indicators (MTI) units. FLSA and MTI failures have been 

identified as having been caused by incorrect connector sleeves materials 

fitted to the MTI units. 

Degradation of the electrical insulation sleeves of the Low-level indication 

lamps on the MTI of the flight deck can cause a short circuit that might result 

in high voltage being conveyed to the high and low level sensors in the wing 

tanks. This condition, if not corrected, could cause the level sensor to heat 

above acceptable limits, possibly resulting in fuel tank explosion, and 

consequent loss of the aeroplane. 

As an interim action, EASA AD 2008-0055 was issued requiring the 

accomplishment of wiring modifications to protect the FLSA and the Flight 

Warning Computers from 115V AC and 28V DC short circuits within the 

cockpit MTI. 

EASA AD 2009-0144 which required the replacement of the affected sensors 

and their harness connectors with modified units in accordance with the 

instructions of Airbus Service Bulletin (SB) A300-28-6095 at original issue or 
EASA AD No : 2010-0175 

EASA Form 110 Page 2/3 

SB A300-28-9013 at original issue, as applicable, was further on cancelled 

because the installation of the new inner tank fused low-level sensors was not 

possible, due to interference between some sensors and a fuel pipe at 

connector level. 

Airbus SB A300-28-6095 and SB A300-28-9013 have been revised to clear 

this interference. The replacement of the affected sensors and their harness 

connectors according to the instructions of these SBs is now possible. 

This AD supersedes AD 2008-0055 and introduces the following actions : 

- expanding of the applicability to A310 aeroplanes; and 

- replacement of the cockpit MTI with a MTI with silicone sleeves and to reinstate the low level warning indication to the cockpit MTI; and 

- replacement of the affected sensors and their harness connectors by fused 

level sensor units for A300-600 and A300-600ST aeroplanes. 

Effective Date: 01 September 2010 

Required Action(s) 

and Compliance 

Time(s): 

Required as indicated, unless accomplished previously : 

(1) For A300-600 aeroplanes on which Airbus modification 06213 has been 

embodied in production and for A300-600ST aeroplanes, 

Within 24 months after the effective date of this AD, 

(1.1) Replace the cockpit MTI in accordance with the instructions defined in 

Airbus SB A300-28-6101 or SB A300-28-9015, as applicable to 

aeroplane model; 

(1.2) Thereafter, replace the high level, low level and overflow sensors, and 

their harness connectors, with fused sensors and new harness 

connectors in accordance with the instructions defined in Airbus SB 

A300-28-6095 Revision 1 or SB A300-28-9013 Revision 1, as 

applicable to aeroplane model; 

(1.3) After the accomplishment of the instructions of paragraph (1.1) and 

(1.2) of this AD, re-instate the low level warning indication to the 

cockpit MTI in accordance with the instructions defined in Airbus SB 

A300-28-6103 Revision 01 or SB A300-28-9017 at original issue, as 

applicable to aeroplane model. 

(2) For A300-600 aeroplanes on which Airbus modification 06213 has not

been embodied in production, 

Within 24 months after the effective date of this AD, 

 (2.1) Replace the cockpit MTI in accordance with the instructions defined in 

Airbus SB A300-28-6101; 

 (2.2) Thereafter, re-instate the low level warning indication to the cockpit 

MTI in accordance with the instructions defined in Airbus SB A300-28-

6103 Revision 01; 

 (2.3) After the accomplishment of the instructions of paragraph (2.1) and 

(2.2) of this AD, replace the high level, low level and overflow sensors, 

and their harness connectors, with fused sensors and new harness 

connectors in accordance with the instructions defined in Airbus SB 

A300-28-6095 Revision 1. 

(3) For A310 aeroplanes, 

Within 24 months after the effective date of this AD, 

replace the cockpit MTI in accordance with the instructions defined in 

Airbus SB A310-28-2167; 

(4) Re-instatement of the low level warning indication to the cockpit MTI 

accomplished before the effective date of this AD in accordance with the 
EASA AD No : 2010-0175 

EASA Form 110 Page 3/3 

instructions defined in Airbus SB A300-28-6103 at original issue is 

considered acceptable for compliance with the requirements of paragraphs 

(1.3) or (2.2) of this AD, as applicable. 

(5) After the effective date of this AD do not install any MTI on aeroplane in the 

cockpit location unless modified in accordance with Smiths Vendor SB 

1404KID-28-466 or 1406KID-28-467 or 1410KID-28-468 or 1420KID-28-

469 or Airbus SB A310-28-2167 or SB A300-28-6101 or SB A300-28-9015, 

as applicable 

Ref. Publications: Airbus Service Bulletin A300-28-6101 at original issue 

Airbus Service Bulletin A310-28-2167 at original issue 

Airbus Service Bulletin A300-28-9015 at original issue 

Airbus Service Bulletin A300-28-6103 at original issue or Revision 1 

Airbus Service Bulletin A300-28-9017 at original issue 

Airbus Service Bulletin A300-28-6095 Revision 1 

Airbus Service Bulletin A300-28-9013 Revision 1 

Smith Vendor Service Bulletin 1404KID-28-466 original issue or Revision 1 

Smith Vendor Service Bulletin 1406KID-28-467 original issue or Revision 1 

Smith Vendor Service Bulletin 1410KID-28-468 original issue or Revision 1 

Smith Vendor Service Bulletin 1420KID-28-469 original issue or Revision 1 

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 16 July 2010 as PAD 10-074 for consultation until 

13 August 2010. 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 SAS – EAW (Airworthiness Office, 

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