EASA AD No.: 2010-0088-E 

EASA Form 111 Page 1/3 

EASA EMERGENCY AIRWORTHINESS DIRECTIVE 

AD No.: 2010-0088-E

Date: 06 May 2010

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 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 130 B4 helicopters

TCDS Number : EASA.R.008 

Foreign AD : Not applicable 

Supersedure : None 

ATA 25 Equipment and Furnishing – Emergency Flotation Gear Wiring – 

Modification

Manufacturer(s): Eurocopter (formerly Eurocopter-France, Aerospatiale) 

Applicability: EC 130 B4 helicopters all serial numbers, if delivered before 15 April 2010 and 

equipped with the flotation gear unit "1G", Part Number (P/N) 350A63256300. 

Reason: 

An uncontrolled in-flight deployment of the emergency flotation gear (not 

armed) on an EC130 B4 helicopter has been reported. The flight crew heard a 

detonation followed by heavy vibrations and noticed that the LH and RH 

emergency flotation gear floats were inflating. 

The investigations carried out on the emergency flotation gear control system, 

revealed that a wire was damaged inside the flotation gear unit "1G". This wire 

was damaged due to interference with the screw securing cable 1GR19E lug 

to the busbar, causing a short circuit in the emergency flotation gear 

deployment activation circuit and the consequent deployment of the 

emergency flotation gear. Additionally, the possibility of interference of “1G” 

unit internal wire harnesses with a fuselage metal structure member (stringer) 

has been identified, which could have the same consequences as above. 

An uncontrolled in-flight deployment of the emergency flotation gear could lead 

to an unexpected deceleration and pitch down movement of the helicopter, 

resulting in a deviation from the intended flight path and reduced controllability 

of the helicopter. 

Consequently, this AD requires a visual inspection of the “1G” unit and the 

associated corrective actions, as applicable and modification of the relevant 
EASA AD No.: 2010-0088-E 

EASA Form 111 Page 2/3 

flotation gear units. 

Effective Date: 10 May 2010 

Required Action(s) 

and Compliance 

Time(s): 

Required as indicated, unless accomplished previously 

(1) Within the next 15 FH after the effective date of this AD, visually inspect 

the flotation gear unit “1G” to determine whether an asterisk (*) follows the 

Part Number (P/N) 350A63256300, in accordance with paragraph 2.B.3.a. 

of Eurocopter EC130 Alert Service Bulletin (ASB) No. 25A037 (the ASB). 

(2) For units that have been identified, as required by paragraph (1) of this 

AD, to have an asterisk (*) following the P/N 350A63256300, before next 

flight, verify that a rubber extrusion is installed on the stringer, in 

accordance with paragraph 2.B.3.a. of the ASB. 

(3) If the inspection as required by paragraph (2) of this AD reveals that no 

rubber extrusion is installed, within 3 months after the effective date of this 

AD, install the rubber extrusion in accordance with paragraph 2.B.5.a. of 

the ASB. 

(4) After modification of a helicopter as required by paragraph (3) of this AD, 

accomplish a functional test in accordance with the instructions of 

paragraph 2.B.6. of the ASB. 

(5) For units that have been identified, as required by paragraph (1) of this 

AD, not to have an asterisk (*) following the P/N 350A63256300, before 

next flight after the inspection as required by paragraph (1) of this AD, 

inspect the internal condition of the flotation gear unit “1G” in accordance 

with paragraph 2.B.3.b. of the ASB. 

(6) Thereafter, analyse the results and perform the relevant corrective 

actions, either once or repetitively as required, in accordance with the 

criteria and the compliance times set forth in the flow chart from the page 

4 (“Interpretation of the results after compliance with instructions given in 

paragraph 2.B.3.b.”) of the ASB. 

(7) Within the next 8 months after the effective date of this AD, unless 

previously accomplished as required by paragraph (6) of this AD, install a 

conforming flotation gear unit “1G” on the helicopter, in accordance with 

paragraph 2.B.2.a of the ASB and install as well the rubber extrusion in 

accordance with paragraph 2.B.5.a. of the ASB. 

(8) After modification of a helicopter as required by paragraph (7) of this AD, 

accomplish a functional test in accordance with the instructions of 

paragraph 2.B.6. of the ASB. 

(9) After the effective date of this AD do not install a flotation gear unit "1G", 

P/N 350A63256300 on any helicopter unless it has been identified, 

modified, and reconditioned, in accordance with the requirements of this 

AD. 

Ref. Publications: 

Eurocopter Emergency EC130 ASB No 25A037, dated 27 April 2010. 

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 substantiated, EASA can approve 

Alternative Methods of Compliance for this AD. 

2. The safety assessment has requested not to implement the full 
EASA AD No.: 2010-0088-E 

EASA Form 111 Page 3/3 

consultation process and an immediate publication and notification. 

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 question 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 10; fax: +33 (0) 4 42 85 99 66; E-mail: 

Directive.technical-support@eurocopter.com