EASA AD No.: 2009 - 0190

EASA Form 110 Page 1/2 

## EASA AIRWORTHINESS DIRECTIVE

AD No.: 2009 - 0190

Date: 26 August 2009

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 participat e 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 aircra ft 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 :

EUROCOPTER Type/Model designation(s) :

EC 120 and EC 130 Helicopters

TCDS Number : DGAC France No. 189; EASA.R.008

Foreign AD : Not applicable

Supersedure : None



### ATA 25 Equipment / Furnishings – Emergency Floatation Gear - Inspection

Manufacturer(s): Eurocopter (formerly Eurocopter France)

Applicability: Eurocopter helicopter models EC 120 B and EC 130 B4, all serial numbers, if equipped with the following emergency floatation gears :
For EC 120 B: - Left hand (LH) floatation gear, part number 215674-0 or 215674-1 or 215674-2, fitted with float part number 215481-0, - Right hand (RH) floatation gear, part number 215675-0 or 215675-1 or 215675-2, fitted with float part number 215482-0.
For EC 130 B4: - LH floatation gear, part number 217227-0, fitted with float part number 217174-0, - RH floatation gear, part number 217228-0, fitted with float part number 217195-0.

Reason: During overhaul of an emergency floatation gear installation, it was impossible to inflate the RH float in a ccordance with the instructions of the equipment manufacturer’s manual. The investigations conducted by the repair centre demonstrated that there was a puncture in one of the compartments of the RH float and damage to several areas of the LH and RH floats due to contact with the protruding sections of the supply bars and banjo unions.EASA AD No.: 2009 - 0190

EASA Form 110 Page 2/2 This condition, if not corrected, coul d lead to insufficient effectiveness on ditching and may lead to instability of the helicopter on the water in case of emergency landing. Pending a modification that will prevent the float fabric covering from chafing on the protruding sections of the emergency gear floatation installation, this AD mandates repetitive inspections of the emergency floatation gear floats and the accomplishment of the relevant corrective actions, as applicable.

Effective Date: 09 September 2009

Required Action(s) and Compliance Time(s): Required as indicated, unless accomplished previously: (1) For emergency floatation gears havin g logged, at the effective date of this AD, more than 250 flying hours (FH) since the first installation on a helicopter or since their last overhaul: Within the next 50 FH or 30 days a fter the effective date of this AD, whichever occurs first, inspect LH and RH emergency floatation gears in accordance with paragraph 2. of Eu rocopter Alert Service Bulletin (ASB) EC 120 ASB 05A011 or EC 130 ASB 05A008, depending on the helicopter type, thereafter repeat t he inspection at intervals not exceeding 300 FH. (2) For emergency floatation gears that have logged, at the effective date of this AD, less than 250 FH since the fi rst installation on a helicopter or since their last overhaul: Before accumulation of 300 FH since the first installation on a helicopter or their last overhaul, inspect LH and RH emergency floatation gears in accordance with paragraph 2. of Eurocopter ASB EC 120 ASB 05A011 or EC 130 ASB 05A008, depending on th e helicopter type, thereafter repeat the inspection at intervals not exceeding 300 FH. (3) In case of discrepancies found during the inspections performed in accordance with paragraphs (1) or (2) of this AD, before next flight accomplish the associated checks and corrective actions in accordance with paragraph 2. of Eurocopter ASB EC 120 ASB 05A011 or EC 130 ASB 05A008, depending on the helicopter type. (4) After the effective date of this AD do not install the affected emergency floatation gears on any helicopter, unless in accordance with the requirements of this AD.

Ref. Publications: EC 120 ASB 05A011 dated 08 June 2009;
EC 130 ASB 05A008 dated 08 June 2009. 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 24 June 2009 as PAD 09-084 for consultation until 24 July 2009. No comments were received during the consultation period. 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 questions concerning the tech nical 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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