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.3 B. In accordance with EC 2042/2003 Annex I, Part M.A.301, the continuing airworthiness of an aircraft s hall be ensured by accomplishing 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 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 2009-01 90 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 Nu mber (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 flot ation gear installation, it was impossible to inflate the RH float in accordance wi th the instructions of the equipment manufacturer’s manual. The investigations conducted by the re pair 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, coul d lead to insufficient effectiveness on ditching and may lead to instability of the helicopter on the water in case ofEASA AD No : 2011 – 0185

EASA Form 110 Page 2/3 emergency landing. To address this potential unsafe cond ition, EASA issued AD 2009-0190 to require repetitive inspections of the em ergency flotation gear floats to detect any chafing between the protruding sect ions 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, an d adds the requirement to modify the emergency flotation gear installation, wh ich 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, de pending on the helicopter type. (4) Within 300 FH or 18 months, whicheve r occurs first after the effective date of this AD, modify the emergency flot ation 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 re petitive 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 Applic ability section of this AD, on anyEASA 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 EC 120 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 tec hnical content of the requirements in this AD, please contact: EUROCOPTER (STDI) - Aéro port 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.