EASA AD No.: 2009-0109-E

EASA Form 111 Page 1/2 

## EASA EMERGENCY AIRW ORTHINESS DIRECTIVE

AD No.: 2009-0109-E

Date: 07 May 2009

Note: This Emergency 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 a ccomplishing any applicable ADs. Consequently, no person may opera te 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) exemptio n]. 

### Type Approval Holder’s Name :

EUROCOPTER Type/Model designation(s) :
SA 365 N and N1 helicopters

TCDS Number : France No 159

Foreign AD : Not applicable

Supersedure : None



### ATA 28 Fuel – High Level Switches / Fuel Transfer between Fuel Tank Groups – Modification / Limitation

Manufacturer(s): Eurocopter France, Aérospatiale

Applicability: SA 365 N and SA 365 N1 helicopters, all serial numbers, except those incorporating modification kit 365A087690.00 or modification 0728B17 (the removal of the two high level switches from helicopters equipped with a crossfeed between the fuel filler necks).

Reason: One SA 365 N operator noted that the high level switch probe unit, located in the rear (right hand) auxiliary fuel tank gr oup had separated. This caused damage to the insulation of the electrical wires which supply the high level indicator light on the fuel control panel during a fuel transfer. This condition, if not detected and corr ected, could lead to exposure of the electrical wires, potentially causing a sh ort circuit and subsequent lighting of the indicator light without the high fuel leve l actually being reached. In addition, a short circuit could become a potential igniti on source inside the fuel tank which, in combination with flammable fuel vapours (if present), could result in a fuel tank explosion and consequent loss of the helicopter. For the reasons described above, this AD requires the disconnection of the high level switches on the affected helicopters. Disconnecting the switches inhibits the high (fuel) level warning system which normally informs the flight crew of the risk of fuel overflowing from the tank vent s. To mitigate that risk, this AD also requires, for certain helicopters, the inst allation of a placard near the fuel panel, limiting the transfer of fuel between f uel tank groups to cases where the receiving fuel tank group contains less than 300 liter (240 kg or 529 lbs.). This AD is considered to be a temporary measure and further action is likely to follow.EASA AD No.: 2009-0109-E

EASA Form 111 Page 2/2 Effective Date: 08 May 2009

Required Action(s) and Compliance Time(s): Required as indicated, unless accomplished previously: Within 10 flight hours or 30 days, whiche ver occurs first after the effective date of this AD, accomplish the following actions, as applicable: (1) On all affected helicopters, disconnect the high level switches in accordance with the instructions of paragraph 2. B.1 of Eurocopter AS365 Alert Service Bulletin (ASB) 01.00.63. (2) On helicopters not equipped with a crossfeed between the fuel filler necks, install a placard near the fuel panel in accordance with the instructions of paragraph 2.B.2 of Eurocopter AS365 ASB 01.00.63.

Ref. Publications: Eurocopter AS365 ASB 01.00.63 dated 05 May 2009. The use of later approved revisions of this document is acceptable for compliance with the requirements of this AD.

Remarks : 1. If requested and appropriately subs tantiated, EASA can approve Alternative Methods of Compliance for this AD. 2. The safety assessment has requested not to implement the full consultation process and an immediate pub lication and notification. 3. Enquiries regarding this AD should be referred to the Airworthiness Directives, Safety Management & Re search Section, Certification Directorate, EASA. E-mail: ADs@easa.europa.eu

. 4. For any question concerning the technica l content of the requirements in this AD, please contact: EUROCOPTER (STDI) – Aéroport de Marseille Provence 13725 Marignane Cedex – France Telephone +33 (0)4 42 85 97 97, Fax +33 (0)4 42 85 99 66 E-mail: Directive.technical-support@eurocopter.com

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