EASA AD No.: 2014

- 0211

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

. : 2014

- 0211

Date: 1 9 September 2014

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 EU 748/2012, P art 21.A.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 ope rate an aircraft to which an AD applies, except in accordan ce 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 :
AIRBUS HELICOPTERS DEUTSCHLAND GmbH Type/Model designation(s) :
MBB

- BK 117 C

- 2 helicopters

TCDS Number: EASA.R.010

F oreign AD: Not applicable

Supersedure: None



### ATA 88 Wiring / Harness

– H oist C ontrol P endant W iring H arness
– Inspection / Modification

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

Applicability: MBB

- BK117 C

- 2 helicopters, all serial numbers, when equipped with optional equipment external mounted hoist system

.

Reason: A n uncommanded hoist cable cut occurred on a n MBB

‐ BK117 C

‐ 2 helicopter.
During the investigation of this incident, chafing was detected on the wiring harness of the hoist control pendant and on the wiring of the +28V wire of the stand

‐ by horizon inside the middle ceiling panel. The wire of the stand

‐ by horizon got in contact with the hoist control pendant wiring harness

, thus causing the uncommanded cable cut.
This condition, if not detected and corrected, could lead to load release, possibly resulting in injury to a human load or to persons on the ground

. To address this unsafe condition, AHD issued Alert Service Bulletin 

### ( ASB ) MBB

‐ BK117 C

‐ 2

‐ 88A

‐ 009 to provide inspection and modification instructions

. For the reason described above, this AD requires a one

- time visual inspection and modification of the hoist control pendant wiring harness.

Effective Date: 22 September 2014EASA AD No.: 2014

- 0211

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 ) B efore the n ext hoist operation after the effective date of this AD, accomplish a o ne

‐ time visual inspection of the hoist control pendant wiring harness i n accordance with the instructions of Section 3.B.2 of ASB MBB

‐ BK117 C

‐ 2

‐ 88A

‐ 009

. ( 2 ) If, during the inspection as required by paragraph (1) of this AD, heavy chafing is found on the h oist control pendant wiring harness

, b efore the next hoist operation

, replace the wiring harness in accordance with the instructions of Section 3.B.2 of ASB MBB

‐ BK117 C

‐ 2

‐ 88A

‐ 009. ( 3 ) Within 3 months after the effective date of this AD , accomplish t he r etrofit of a protection sleeve to the hoist control pendant wiring harness in accordance with the instructions of Section 3.B.3 of ASB MBB

‐ BK117 C

‐ 2

‐ 88A

‐ 009. ( 4 ) From the effective date of this AD, installation of a hoist control pendant wiring harness is allowed, provided the harness is fitted with a protection sleeve as required by paragraph (3) of this AD prior to installation.

Ref. Public ations: Airbus Helicopters Deutschland ASB MBB

‐ BK117 C

‐ 2

‐ 88A

‐ 009 original issue dated 18 June 2014. 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, 86607 Donauwör th, Federal Republic of Germany Telephone: + 49 (0)151 1422 8976; Facsimile: + 49 (0)906 71 4111.