EASA AD No.: 2012

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CAP.0011 1

- 001 © European A viation Safety Agency. All rights reserved. 1 / 3 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. 

## EASA EMERGENCY AIRWORTHINESS DIRECTIVE

AD No .: 201 2

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Date: 13 July 201 2

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 continuin g 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]

. 

### Design Approval Holder’s Name :

EUROCOPTER Type/Model designation(s) :

AS 332 and EC 225 helicopters

TCDS Number: EASA.R.00 2

Foreign AD: Not applicable

Supersedure: This AD supersedes EASA AD 2009

- 0 099

- E dated 23 April 20 09.



### ATA 63 Main Rotor Drive

– Main Gear Box , Intermediate gear Box and Tail

Gear Box

– Modifica tion / Inspection

Manufacturer(s): Eurocopter (former ly EUROCOPTER France)

Applicability: AS 332 C, AS 332 C1, AS 332 L, AS 332 L1, AS 332 L2 and EC 225 LP helicopters, all serial numbers

.

Reason: F ollowing an accident with an AS 332 L2 helicopter on 1 April 2009, off the coast of Scotland near Aberdeen

, t he preliminary results of the investigation s showe d a failure within the epicyclic reduction gear module of the Main Gear Box (MGB) which resulted in the rupture of the MGB case and allowed the main rotor head to separate from the helicopter.

To address th is potential unsafe condition on the AS 332 L2 and EC 225 LP helicopter models equipped with a similar MGB

, enhancement of the means for detection of MGB contamination and degradation was deemed of the utmost importance.
As an initial precautionary measure , EASA issued AD 2009

- 0087

- E with that aim. Additionally, EASA issued AD 2009

- 0095

- E to require a one

- time inspection to detect particles in the MGB epicyclic reduction gear module

. Subsequently , EASA issued AD 2009

- 0099

- E , which retain ed the main requir ements of ADs 2009

- 0087

- E and 2009

- 0095

- E, which were superseded, and require d modification of the chip collector inside the MGB ( located between the epicyclic module and the main module ) to enhance the early detection capability of the magnetic plug s of t he gearbox sump and the epicyclic module. To that aim, AD 2009

- 0099

- E require d removing the magnetic elements installed on the chip collector and the flanged edged fromEASA AD No.: 2012

- 01 29

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CAP.0011 1

- 001 © European A viation Safety Agency. All rights reserved. 2 / 3 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. the chip collector ( equivalent to production MOD 07 52522). After accomplishment of the modi fication, the AD also required monitor ing of the MGB epicyclic reduction gear module magnetic plug of the affected helicopter models

. Since issuance of EASA AD 2009

- 0099

- E

, the UK Air Accident Investigation B oard published the final accident report

. On the basis of these investigation findings

, it has been decide d to standardize the intervals of the visual checks of all electrical and non

- electrical chip detectors, and to require this check for all models of the Super

- Puma helicopter family

, in order to increase the likelihood of detecting any adhered particle s

. T his action must be accomplished on all rotor drive system gear box es , i.e. on the M G B , but also on the Intermediate Gear Box (IGB) and the Tail Gear Box (TGB).
For the reasons described above, t his new AD ret ains the requirement for the accomplishment of MOD 0752522 of AD 2009

- 0 099

- E , which is supersede d

, ex pa nds the Applicability and requires repetitive visual checks of all electrical and non

- electrical chip detectors installed on MGB, IGB and T GB

.

Effective Date: 1 5 Ju ly 2012

Required Action(s) and Compliance Time(s): Required as indicated, unless accomplished previously:
(1) For AS 332 L2 and EC 225 LP helicopters

, before next flight after 24 April 2009 [ the effective date of AD 2009

- 0099

- E] , modify the MGB epicyclic reduction gear module (MOD 07 52522) in accordance with the instructions of paragr aph 2.B of Eurocopter AS332 Alert Service Bulletin (ASB) No. 05.00.81 revision 3, or EC225 ASB No. 05A017 revision 3 , as applicable to helicopter mo del

. (2) M odif ication of a MGB epicyclic reduction gear module (MOD 07 52522)

, accomplished before the effective date of this AD, in accordance with the instructions of Eurocopter AS332 ASB No. 05.00.81 revision 2, or EC225 ASB No. 05A017 revision 2 , as app licable to helicopter model, is acceptable for compliance with the modification as required by paragraph (1) of this AD.
( 3 ) Afte r 24 April 2009 [ the effective date of AD 2009

- 0099

- E] , do not install on any AS 332 L2 and EC 225 LP helicopters a MGB, unless it has been modified in production with MOD 07 52522 or in service in accordance with the instructions of Eur ocopter AS332 ASB No. 05.00.81 revision 2 or revision 3, or EC225 ASB No. 05A017 revision 2 or revision 3 , as applicable to helicopter model

. ( 4 ) F or all helicopters

, within the compliance times after the effective date of this AD

, as specified in Appendix 1 of this AD for initial and repetitive inspections , visually check for no particles all non

- electrical and electrical chip detectors

, in accordan ce with the instructions of paragraph 3.B of Eurocopter ASB No. AS332.05.00.94 or ASB No. EC225.05A029, as applicable to helicopter model, as listed in that Appendix 1 of this AD

. ( 5 ) If, during any inspection as required by paragraph ( 4 ) of this AD, a par ticle is found, before next flight, accomplish the applicable maintenance actions in accordance with the instructions of paragraph 3.B of Eurocopter ASB No. AS332. 05.00.94 and ASB No. EC225. 05A029 , as applicable to helicopter model

. ( 6) Accomplishment of a pplicable maintenance actions as required by paragraph (5 ) of this AD does not constitutes termination action for the repetitive visual checks as required by (4) of this AD.

Ref. Public ations: Eurocopter AS332 ASB No. 0 5 .00.8 1 Revision 3 dated 13 July 201 2 ; Eurocopter EC225 ASB No. 05 A0 17 Revision 3 dated 13 July 2012 ; Eurocopter ASB No. AS332. 05.00.94 Revision 0 dated 13 July 2012;EASA AD No.: 2012

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CAP.0011 1

- 001 © European A viation Safety Agency. All rights reserved. 3 / 3 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. Eurocopter ASB No. EC225. 05A029 Revision 0 dated 13 July 2012.
The use of later approved revisions of these documents is acce ptable 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 publ ication 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. Fo r any question concerning the technical content of the requirements in this AD, please contact: EUROCOPTER (STDI)

– Aéroport de Marseille Provence 13725 Marignane Ce dex, France; telephone +33 (4) 4 2 85 97 97; facsimile +33 (4) 42 85 99 66; E

- mail: Directive.technical

- support@eurocopter.com

.

Appendix 1

– Chip Detectors visual ins pections (initial and repetitive checks)

Helicopter model(s) Chip Detectors of Type of Chip Detectors Inspection s after the effective date of this AD

AS 332 C,
AS 332 C1,
AS 332 L,

AS 332 L1

, - Mast tapered housing Non

- Electrical Chip Detectors

or Electrical Chip Detectors

, not connected to instrument panel caution light (for EuroHums or EuroArms systems only) Wi thin 25 FH or before next scheduled chip detector inspection ,whichever occurs first, and thereafter at intervals not exceeding 25 FH
- MGB bottom casing,

- IGB and TGB

- MGB bottom casing,

- IGB and TGB Electrical Chip Detectors

, connected to instru ment panel caution light Within 50 FH or before next scheduled chip detector inspection ,whichever occurs first, and thereafter at intervals not exceeding 50 FH

AS 332 L2 - Mast tapered housing

- MGB epicyclic module,

- IGB and TGB Non

- Electrical Chip Det ectors

or Electrical Chip Detectors

, not connected to instrument panel caution light (for Eu roHums or EuroArms systems only) Within 25 FH or before next scheduled chip detector inspection ,whichever occurs first, and thereafter at intervals not exceeding 25 FH

- MGB bottom casing Electrical Chip Detectors Within 50 FH or before next scheduled chip detector inspection ,whichever occurs first, and thereafter at intervals not exceeding 50 FH

EC 225 LP - Mast tapered housing

- MGB epicyclic module

- MGB bot tom casing

,

- IGB and TGB Electrical Chip Detectors Within 50 FH or before next scheduled chip detector inspection ,whichever occurs first, and thereafter at intervals not exceeding 50 FH