EASA AD No.: 2012-0046-E 

EASA Form 111 Page 1/3 

EASA EMERGENCY AIRWORTHINESS DIRECTIVE 

AD No.: 2012-0046-E 

Date: 21 March 2012 

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) : 

AS 332 helicopters 

TCDS Number : EASA.R.002 

Foreign AD : Not applicable 

Supersedure : None 

ATA 53 Fuselage –Bottom Structure Longitudinal Beams Y350 – Inspection 

/ Repair 

Manufacturer(s): Eurocopter (formerly EUROCOPTER France) 

Applicability: AS 332 C1 and AS 332 L1 helicopters, serial numbers as specified in 

Eurocopter AS332 Alert Service Bulletin (ASB) 01.00.81. 

Reason: Eurocopter recently found on the production line that non-conforming rivets 

have been installed on the Right Hand (RH) and Left Hand (LH) longitudinal 

beams Y350 of the bottom structure, between sections X4780 and X5295, on 

an AS332 helicopter. 

The investigation results showed that on a limited number of helicopters, 

although a production modification (OP 21132, 07 21432, OP 22383, 07 23587 

or 07 26082) involving the replacement of the 3.2 mm diameter rivets with 4.8 

mm diameter rivets was recorded in the helicopter documents, the actual 

replacement of the rivets had not been embodied on the fuselage. 

This condition, if not detected and corrected, leads to significant reduction in 

safety margins during sling operations and may over time cause failure of the 

web/flange assembly connections of the beams Y350, possibly resulting in loss 

of control of the helicopter. 

For the reasons described above, this Emergency AD, pending inspection of 

the helicopter structure and replacement of the rivets, prohibits flight for 

helicopters having accumulated more than 45 000 sling operation cycles and 

requires for the others to limit the use of the 3-ton sling to external loads of 2.28 

tons maximum. In addition, this AD requires inspection and modification of the 

helicopters having logged less than 45 000 sling operation cycles and, in case 

of findings, to prohibit flight or sling operation until the rivets are replaced. The 

rivets replacement is also required for helicopters having never performed sling 

operation.
EASA AD No.: 2012-0046-E 

EASA Form 111 Page 2/3 

Effective Date: 23 March 2012 

Required Action(s) 

and Compliance 

Time(s): 

Required as indicated, unless accomplished previously: 

(1) For helicopters having accumulated, on the effective date of this AD, 

45 000 or more sling operation cycles, before next flight, accomplish the 

following actions concurrently: 

 Note: A single flight, not exceeding 10 flight hours (FH) is allowed to ferry 

the helicopter to a location where maintenance can be accomplished. 

(1.1) Inspect the rivets installed on the RH and LH longitudinal beams 

Y350 of the bottom structure in accordance with the instruction of the 

paragraphs 3.B.1 and 3.B.3 of Eurocopter AS332 ASB 01.00.81; and 

(1.2) Report any observed damage to Eurocopter and restore the 

condition of the helicopter in accordance with EUROCOPTER 

defined maintenance and/or repair solution; and 

(1.3) Replace the rivets of the RH and LH longitudinal beams Y350 of the 

bottom structure in accordance with the instruction of the paragraph 

3.B.7 of Eurocopter AS332 ASB 01.00.81. 

(2) For all other helicopters, within 10 FH after the effective date of this AD, 

limit the use of the 3-ton sling to external loads of 2.28 tons maximum by 

temporarily affixing labels on the helicopter and amending its Rotorcraft 

Flight Manual (RFM) in accordance with the instructions of paragraph 3.B.2 

of Eurocopter AS332 ASB 01.00.81. 

(3) For helicopters having accumulated, on the effective date of this AD, less 

than 45 000 sling operation cycles, after implementation of the sling 

limitation as required by paragraph (2) of this AD, within 100 FH after the 

effective date of this AD, comply with the requirement of paragraph (1.1) of 

this AD. 

(3.1) If, during the inspection as required by paragraph (3) of this AD, 

loose rivets or missing rivets or cracks are found, before next flight, 

comply with the requirements of paragraphs (1.2) and (1.3) of this 

AD. 

(3.2) If, during the inspection as required by paragraph (3) of this AD, rivet 

black mark is found, before next flight, prohibit sling operation by 

replacing labels and RFM amendment required by paragraph (2) of 

this AD, with other temporary labels and RFM amendment in 

accordance with the instructions of paragraph 3.B.4 of Eurocopter 

AS332 ASB 01.00.81; and 

 before resuming sling operation, or within 24 months after the 

effective date of this AD, whichever occurs first, comply with the 

requirements of paragraphs (1.2) and (1.3) of this AD. 

(3.3) If, during the inspection as required by paragraph (3) of this AD, no 

rivet black marks or loose/missing rivets or cracks are found, within 

24 months after the effective date of this AD, comply with the 

requirements of paragraph (1.3) of this AD. 

(4) For the helicopters having never performed sling operation before the 

effective date of this AD, after implementation of the sling limitation as 

required by paragraph (2) of this AD, within 24 months after the effective 

date of this AD, comply with the requirements of paragraph (1.3) of this AD. 

(5) After replacement of the rivets of the RH and LH longitudinal beams Y350 

of the bottom structure, as required by paragraph (1.3) of this AD, the sling 

operation limitations as required by paragraphs (2) or (3.2) of this AD, as 

applicable, are cancelled, and the temporary labels and RFM amendment 

can be removed from the helicopter. 
EASA AD No.: 2012-0046-E 

EASA Form 111 Page 3/3 

Ref. Publications: Eurocopter AS332 ASB 01.00.81, Revision 0 dated 19 March 2012 

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 consultation 

process and an immediate publication and notification. 

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; telephone +33 (4) 12 85 97 97; facsimile +33 (4) 

85 99 66; E-mail: Directive.technical-support@eurocopter.com.