EASA AD No.: 2015-0153-E

TE.CAP.00111-004 © European Aviation Safety Agency. All rights reserved. 1/2 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. 

## EASA EMERGENCY AIRWORTHINESS DIRECTIVE

AD No.: 2015-0153-E

Date: 24 July 2015

Note: This Emergency Airworthiness Directive (AD) i s issued by EASA, acting in accordance with Regulation (EC) No 216/2008 on behalf of the E uropean 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 EU 748/2012, P art 21.A.3B. In accordance with EU 1321/2014 Annex I, Part M.A.301, the continuing airworthiness of an aircraft shall be en sured by accomplishing any applicable ADs. Conseque ntly, no person may operate an aircraft to which an AD applies, except in accordan ce with the requirements of that AD, unless otherwi se specified by the Agency [EU 1321/2014 Annex I, Part M.A.303] or agreed with th e Authority of the State of Registry [EC 216/2008, Article 14(4) exemption].


### Design Approval Holder’s Name:
AIRBUS HELICOPTERS Type/Model designation(s): AS 332 helicopters

TCDS Number: EASA.R.002

Foreign AD: Not applicable

Supersedure: None



### ATA 64 Tail Rotor – Rotor Blades – Inspection

Manufacturer(s): Airbus Helicopters (formerly Euroc opter, Eurocopter France, Aerospatiale).

Applicability: AS 332 C, AS 332 C1, AS 332 L, and A S 332 L1 helicopters, equipped with tail rotor de-icing installation unit Part Number (P/N) 204ZP01Y01 and tail rotor blade P/N 332A12-0055-XX (where XX represents any d ash number) (type A10).

Reason: An occurrence was reported involving tail r otor blade overheat and consequent damage after application of Alternated Current Grou nd Power Unit (AC GPU) external power source 115V/400 H z on ground following a flight during which the de-icing system of the helicopter was operated. Subsequent analysis determined the power supply box failure (stuck in a “closed” position) as the cause for the uncontrolled power supply to the roto r blade de-icing system. In case the rotor blade de-icing system is erroneously activated, as a result of application of AC GPU external power source 115V/40 0 H z on ground, during the preparation for flight with the rotors stationa ry, the crew is not able to detect the fumes or smells coming from the tail rotor and therefore to detect a possible damage of a tail rotor blade.
This condition, if not detected and corrected, coul d lead to structural damage of tail rotor blades resulting in significant vibratio ns and reduced control of the helicopter. To address this potential unsafe condition, Airbus Helicopters issued Alert Service Bulletin (ASB) AS332-05.01.02 to provide in structions for inspection of tail rotor blades and, depending on findings, corre ctive actions. For the reasons described above, this AD requires u n-scheduled inspections ofEASA AD No.: 2015-0153-E

TE.CAP.00111-004 © European Aviation Safety Agency. All rights reserved. 2/2 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. the tail rotor blades and, depending on findings, c orrective action.

This AD is considered to be an interim action and f urther AD action may follow.

Effective Date: 27 July 2015

Required Action(s) and Compliance Time(s): Required as indicated, unless accomplished previous ly: (1) From the effective date of this AD, before each engine start after any of the events as specified in paragraph (1.1) or (1.2) of this AD, inspect each tail rotor blade in accordance with the instructions of paragraph 3.B.2 of Airbus Helicopters ASB AS332-05.01.02. (1.1) Application of an AC GPU external power sourc e 115V/400 H z with the rotor stationary after the de-icing system was operated (in-flight or on ground), or (1.2) Application of an AC GPU external power sourc e 115V/400H z with the rotor stationary after accomplishment of the ta il rotor de-icing system test (with spinning or stationary rotor). (2) If, during any inspection as required by paragr aph (1) of this AD, any discrepancy is detected, as defined in Airbus Helic opters ASB AS332-05.01.02, accomplish all the corrective actio ns in accordance with the instructions of paragraph 3.B.2 of Airbus Helic opters ASB AS332-05.01.02.

Ref. Publications: Airbus Helicopters ASB AS332-05. 01.02 original issue, dated 22 July 2015. The use of later approved revisions of this documen t is acceptable for compliance with the requirements of this AD.

Remarks: 1. If requested and appropriately substantiated, EA SA can approve Alternative Methods of Compliance for this AD. 2. The results of the safety assessment have indica ted the need for immediate publication and notification, without the full public consultation process. 3. Enquiries regarding this AD should be referred t o the Safety Information Section, Executive Directorate, EASA. E-mail: ADs@easa.europa.eu. 4. For any question concerning the technical conten t of the requirements in this AD, please contact: Airbus Helicopters (EBSESB) – Aéroport de Marseille Provence 13725 Marignane Cedex, France; Telephone +33 (4) 42 85 97 97; Fax +33 (4) 42 85 99 66; E-mail: Directive.technical-support@airbus.com

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