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 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 : 

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 accordance 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. 

SUPERSEDED
EASA AD No.: 2009 - 0190 

EASA Form 110 Page 2/2 

This condition, if not corrected, could 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 having 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 after the effective date of this AD, 

whichever occurs first, inspect LH and RH emergency floatation gears in 

accordance with paragraph 2. of Eurocopter Alert Service Bulletin (ASB) 

EC 120 ASB 05A011 or EC 130 ASB 05A008, depending on the 

helicopter type, thereafter repeat the 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 first 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 the 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 & Research Section, Certification 

Directorate, EASA. E-mail: ADs@easa.europa.eu. 

4. For any questions concerning the technical 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.

SUPERSEDED