EASA AD No : 2011 – 0185 

EASA Form 110 Page 1/3 

EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2011-0185 

Date: 23 September 2011 

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 Numbers: DGAC France No. 189; EASA.R.008 

Foreign AD: Not applicable 

Supersedure: This AD supersedes EASA AD 2009-0190 dated 26 August 2009. 

ATA 25 Equipment / Furnishings – Emergency Flotation Gear – Inspection 

/ Modification 

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 flotation gears : 

For EC 120 B helicopters: 

- Left hand (LH) flotation gear, Part Number (P/N) 215674-0, or P/N 215674-1, 

or P/N 215674-2, fitted with float P/N 215481-0, 

- Right hand (RH) flotation gear, P/N 215675-0, or P/N 215675-1, or P/N 

215675-2, fitted with float P/N 215482-0. 

For EC 130 B4 helicopters: 

- LH flotation gear, P/N 217227-0, fitted with float P/N 217174-0, 

- RH flotation gear, P/N 217228-0, fitted with float P/N 217195-0. 

Reason: During overhaul of an emergency flotation 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. 

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 
EASA AD No : 2011 – 0185 

EASA Form 110 Page 2/3 

emergency landing. 

To address this potential unsafe condition, EASA issued AD 2009-0190 to 

require repetitive inspections of the emergency flotation gear floats to detect 

any chafing between the protruding sections of the installation and the fabric 

covering of the floats, and to correct any discrepancies found. 

Since that AD was issued, AERAZUR, the manufacturer of the emergency 

flotation gear installation, has developed a modification which eliminates 

interference between the blunt parts of the emergency flotation gear 

installation and the fabric covering of the floats. 

For the reasons described above, this AD retains the requirements of EASA 

AD 2009-0190, which is superseded, and adds the requirement to modify the 

emergency flotation gear installation, which constitutes terminating action for 

the repetitive inspections. 

Effective Date: 07 October 2011 

Required Action(s) 

and Compliance 

Time(s): 

Required as indicated, unless accomplished previously: 

(1) Initially, within the time indicated in Table 1 of this AD, as applicable, 

inspect the LH and RH emergency flotation gears in accordance with the 

instructions of paragraph (§) 2. of Eurocopter EC120 Alert Service Bulletin 

(ASB) 05A011 or EC130 ASB 05A008, depending on the helicopter type. 

Table 1 – Initial Inspection 

Flight hours (FH) accumulated 

by the emergency floatation 

gears on 09 September 2009 

[the effective date of EASA AD 

2009-0190] since the first 

installation on a helicopter, or 

since last flotation gear overhaul

Compliance time 

250 FH or more Within 50 FH or 30 days after 09 

September 2009 [the effective date 

of EASA AD 2009-0190], 

whichever occurs first 

Less than 250 FH Before accumulating 300 FH since 

the first installation on a helicopter, 

or since last flotation gear overhaul 

(2) Thereafter, at intervals not exceeding 300 FH, repeat the inspection as 

specified in paragraph (1) of this AD. 

(3) If, during any inspection as required by paragraphs (1) or (2) of this AD, 

discrepancies are detected, before next flight, accomplish the associated 

checks and corrective actions in accordance with § 2 of Eurocopter EC120 

ASB 05A011 or EC130 ASB 05A008, depending on the helicopter type. 

(4) Within 300 FH or 18 months, whichever occurs first after the effective date 

of this AD, modify the emergency flotation gear installation in accordance 

with the instructions of § 3.B.1 of Eurocopter EC120 ASB 25A026 or 

EC130 ASB 25A042, depending on the helicopter type. 

(5) Modification of a helicopter as required by paragraph (4) of this AD 

constitutes terminating action for the repetitive inspection requirements of 

paragraph (1) and (2) of this AD for that helicopter. 

(6) After the effective date of this AD, do not install emergency flotation gear, 

as identified by P/N in the Applicability section of this AD, on any 
EASA AD No : 2011 – 0185 

EASA Form 110 Page 3/3 

helicopter, unless it has been modified in accordance with the instructions 

of § 3.B of Eurocopter EC120 ASB 25A026 or EC130 ASB 25A042, 

depending on the helicopter type.

Ref. Publications: EC 120 ASB 05A011 dated 08 June 2009. 

EC 120 ASB 25A026 dated 11 July 2011. 

EC 130 ASB 05A008 dated 08 June 2009. 

EC 130 ASB 25A042 dated 11 July 2011. 

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 18 August 2011 as PAD 11-089 for consultation 

until 15 September 2011. No comments were received during the 

consultation period. 

3. Enquiries regarding this AD should be referred to the Safety Information 

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

4. For any question concerning the technical content of the requirements in 

this AD, please contact: 

EUROCOPTER (STDI) - Aéroport de Marseille Provence 

13725 Marignane Cedex - France 

Tel: +33 (0) 4 42 85 97 97 - Fax: +33 (0) 4 42 85 99 66 

E-mail: Directive.technical-support@eurocopter.com.