EASA AD No.: 2015-0153-E 

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EASA EMERGENCY AIRWORTHINESS DIRECTIVE 

AD No.: 2015-0153-E 

Date: 24 July 2015 

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 EU 748/2012, Part 21.A.3B. In accordance with EU 1321/2014 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 [EU 

1321/2014 Annex I, Part M.A.303] or agreed with the 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 Eurocopter, Eurocopter France, Aerospatiale). 

Applicability: AS 332 C, AS 332 C1, AS 332 L, and AS 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 dash number) (type 

A10). 

Reason: An occurrence was reported involving tail rotor blade overheat and consequent 

damage after application of Alternated Current Ground Power Unit (AC GPU) 

external power source 115V/400 Hz 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 rotor 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/400 Hz on ground, during 

the preparation for flight with the rotors stationary, 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, could lead to structural damage of 

tail rotor blades resulting in significant vibrations 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 instructions for inspection of 

tail rotor blades and, depending on findings, corrective actions. 

For the reasons described above, this AD requires un-scheduled inspections of 
EASA AD No.: 2015-0153-E 

TE.CAP.00111-004 © European Aviation Safety Agency. All rights reserved. 2/2 

Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.

the tail rotor blades and, depending on findings, corrective action. 

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

Effective Date: 27 July 2015 

Required Action(s) 

and Compliance 

Time(s): 

Required as indicated, unless accomplished previously: 

(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 source 115V/400 Hz 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 source 115V/400Hz with 

the rotor stationary after accomplishment of the tail rotor de-icing 

system test (with spinning or stationary rotor). 

(2) If, during any inspection as required by paragraph (1) of this AD, any 

discrepancy is detected, as defined in Airbus Helicopters ASB 

AS332-05.01.02, accomplish all the corrective actions in accordance with 

the instructions of paragraph 3.B.2 of Airbus Helicopters 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 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 results of the safety assessment have indicated the need for 

immediate publication and notification, without the full public consultation 

process. 

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: 

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.