EASA AD No.: 2015

- 01 98

TE. CAP.00110

- 00 4 © European Aviation Safety Agency. All rights reserved. 1 / 2 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. 

## EASA AIRWORTHINESS DIRECTIVE

AD No

. : 2015 - 01 98

Date: 30 September 2015

Note: This 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 E U 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 ope rate 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 DEUTSCHLAND GmbH Type/Model designation(s) : MBB

- BK 117 D

- 2 helicopters

TCDS Number: EASA.R.010

F oreign AD: Not applicable
Supersedure: None



### ATA 71 Power P lant

– Engine M ount B ushings

– Inspection

Manufacturer(s): Airbus Helicopters Deutschland GmbH (AHD) , forme rly Eurocopter Deutschland GmbH

. Applicability: MBB

- BK 117 D

- 2 helicopters, all serial numbers.

Reason: During a pre

- flight check of an MBB

- BK 117 D

- 2 helicopter , an engine mount bushing of one engine was found delaminated. During additional investigation, further cases of delaminated engine mount bushings were detected. This condition, if not detected and corrected, may lead to crack s and , eventually , failure of the engine mount front support pin s , possibly resulting in loss of control of the helicopter

. To address this potential unsafe condition, AHD issued Alert Service Bulletin (ASB) MBB

- BK117 D

- 2

- 71A

- 002 to provide instructions to inspect the engine mounts bushing

. For the reasons described above, this AD requires accomplishment of repetitive inspections of the engine mounts bushings and, depending o n findings, the accomplishment of applicable corrective action ( s )

. Effective Date: 14 October 2015EASA AD No.: 2015

- 01 98

TE. CAP.00110

- 00 4 © European Aviation Safety Agency. All rights reserved. 2 / 2 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. Required A ction(s) and Compliance Time(s) : Required as indicated, unless accomplished previously: (1) Within 50 flight hours (FH) after the effective date of this AD, and , thereafter , at intervals not to exceed 50 FH (see N ote 1 of this AD ) , inspect the bushings of the inner and outer forward trusses of both engine s , in accordance with the instructions of paragraph 3.B.2 of AHD ASB MBB

- BK117 D

- 2

- 71A

- 002

. Note 1 : A non

- cumulative tolerance of 10 FH may be applied to the compliance times specified in paragraph (1) of this AD to allow synchronization of the required inspections with other maintenance tasks for which a noncumulative tolerance is already granted in the applicable Maintenance Manual. (2 ) If, during any inspection as required by paragraph (1) of this AD, any defective bushing is found, before next flight , accomplish the applicable corrective action ( s ) in accordance with the instructions of section 3.B.2 of AHD ASB MBB

- BK117 D

- 2

- 71A

- 002

. ( 3 ) Corrective action(s) accomplished on a helicopter , as required by paragraph (2) of this AD , do not constitute terminating action for the repetitive inspections as required by paragraph (1) of this AD for that helicopter

. Ref. Publications: AHD ASB MBB

- BK117 D

- 2

- 71A

- 002 original issue , dated 28 September 2015. The use of later approved revisions of th is 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. Based on t he required actions and the compliance time, EASA have decided to issue a Final AD with Request for Comments , postponing the public consultation process until after publication

. 3. Enquiries regarding this A D should be referred to the Safety Information Section, Certification 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 Deutschland GmbH, Industriestrasse 4, 8660 9 Donauwörth, Germany Telephone: + 49 (0)151 1422 8976; Facsimile: + 49 (0)906 71 4111