EASA AD No.: 2015-0019R1

TE.CAP.00110-004 © European Aviation Safety Agency. All rights reserved. 1/3 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. 

## EASA AIRWORTHINESS DIRECTIVE

AD No.: 2015-0019R1

Date: 13 February 2015

Note: This Airworthiness Directive (AD) is issued b y EASA, acting in accordance with Regulation (EC) No 216/2008 on behalf of the European Communit y, its Member States and of the European third countries that participate in the ac tivities 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 accor dance with the requirements of that AD, unless othe rwise specified by the Agency [EU 1321/2014 Annex I, Part M.A.303] or agreed wit h the Authority of the State of Registry [EC 216/20 08, Article 14(4) exemption].



### Design Approval Holder’s Name:

AIRBUS HELICOPTERS DEUTSCHLAND GmbH Type/Model designation(s):
MBB-BK117 helicopters

TCDS Number: EASA.R.010

Foreign AD: Not applicable

Revision: This AD revises EASA Emergency AD 2015-00 19-E dated 05 February 2015,

which superseded EASA AD 2014-0057 dated 06 March 2 014, including the Correction dated 07 March 2014.



### ATA 85 Optional Equipment – External Rescue Hoist System – Inspection / Modification

Manufacturer(s): Airbus Helicopters Deutschland Gmb H (AHD) (formerly Eurocopter Deutschland GmbH), Airbus Helicopters Inc. (formerl y American Eurocopter LLC).

Applicability: MBB-BK117 C-2 and MBB-BK117 D-2 heli copters, all serial numbers, if equipped with a Goodrich external mounted hoist.

Reason: In an incident involving an MBB-BK 117 C-2 helicopter, the rescue hoist damper unit detached from the cable when the hoist damper was lifted by hand (no load attached). Subsequent investigation reveal ed that the detachment occurred because a retaining ring inside the damper unit was not located at its correct installation position. It was determined th at the displacement of the retaining ring may occur as a maintenance induced e rror, or as a result of retaining ring interaction with the bonding strap u nit during operation.
This condition, if not detected and corrected, coul d lead to the detachment of an external load or person from the helicopter hois t, possibly resulting in personal injury, or injury to persons on the ground

. To address this potential unsafe condition, EASA is sued AD 2014-0046-E applicable to MBB BK117 C-2 helicopters to require replacement of the affected rescue hoist damper units, or deactivation of the r escue hoist. That AD was superseded by EASA AD 2014-0057 (later corrected), which, in order to reactivate the hoist damper unit, required modifica tion of the bonding strap unit, installation of an improved retaining ring and post -modification repetitive inspections.EASA AD No.: 2015-0019R1

TE.CAP.00110-004 © European Aviation Safety Agency. All rights reserved. 2/3 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. Since that AD was issued, a new occurrence of hoist damper unit detachment was reported, involving an already modified hoist. Moreover, the affected modified hoist was also approved for installation o n the new model MBB BK117 D-2.
Prompted by the new occurrence of the hoist damper unit detachment, AHD issued Emergency Alert Service Bulletin (ASB) MBB-B K117 C-2-85A-041 Revision 3 and ASB MBB-BK117 D-2-85A-002 original i ssue. Consequently, EASA issued Emergency AD 2015-0019-E, superseding E ASA AD 2014-0057, to require replacement of the affected rescue hoist damper units, or deactivation of the affected rescue hoist, also app licable for MBB-BK117 D-2 helicopters.
After that AD was issued, AHD developed a new singl e-piece retainer, Part Number (P/N) B851M2060201, installation of which st rengthens the interconnection of hoist damper unit and attached c able.

For the reason described above, this AD is revised to introduce installation of the single-piece retainer as an acceptable alternat ive method of compliance with the requirements of this AD. This AD also allo ws installation of certain rescue hoist damper units, provided those units are equipped with the new single-piece retainer P/N B851M2060201.

Effective Date: Revision 1: 13 February 2015
Original issue: 07 February 2015

Required Action(s) and Compliance Time(s): Required as indicated, unless accomplished previous ly:
(1) For helicopters equipped with (optional) rescue hoist damper unit P/N 44307-480, P/N 44307-480-1 or P/N 44307-480-2, as a pplicable for helicopter model, before the next hoist operation a fter 07 February 2015 [the effective date of this AD at original issue], accomplish one of the actions as specified in paragraph (1.1) or (1.2) or (1.3) of this AD, in accordance with the instructions of AHD ASB MBB-BK1 17 C-2-85A-041, or ASB MBB-BK117 D-2-85A-002:
(1.1) Replace a Goodrich hoist damper unit with a s erviceable part,
(1.2) Deactivate the rescue hoist,
(1.3) Modify the hoist damper unit by replacing spl it retainer P/N 42305-286 with a single-piece retainer 

### P/N B851M2060201.
(2) From 07 February 2015 [the effective date of th is AD at original issue], it is allowed to install or activate on a helicopter a re scue hoist damper unit P/N 44307-480, P/N 44307-480-1 or P/N 44307-480-2 or an external hoist incorporating a hoist damper unit P/N 44307-480, P/ N 44307-480-1 or P/N 44307-480-2, provided the hoist damper is equipped with a single-piece retainer P/N B851M2060201.

Ref. Publications: AHD ASB MBB-BK117 C-2-85A-041 Re vision 3, dated 03 February 2015, or Revision 4, dated 12 February 2015.
AHD ASB MBB-BK117 D-2-85A-002 original issue, dated 03 February 2015, or Revision 1, dated 12 February 2015.
The use of later approved revisions of these docume nts 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. Based on the required actions and the compliance time, EASA have decided to issue a Final AD with Request for Commen ts, postponing the public consultation process until after publication

.EASA AD No.: 2015-0019R1

TE.CAP.00110-004 © European Aviation Safety Agency. All rights reserved. 3/3 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. 3. Enquiries regarding this AD should be referred t o the Safety Information Section, Certification 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 Deutschland GmbH, Industriestras se 4, 86607 Donauwörth, Federal Republic of Germany Telephone: + 49 (0)151-1422 8976; Facsimile: + 49 ( 0)906-71 4111.