EASA AD No.: 2014-0246

TE.CAP.00110-004 © European Aviation Safety Agency. All rights reserved. 1/2 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. 

## EASA AIRWORTHINESS DIRECTIVE

AD No.: 2014-0246

Date: 12 November 2014

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 EC 2042/2003 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 accordan ce with the requirements of that AD, unless otherwi se 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, A rticle 14(4) exemption].



### Design Approval Holder’s Name:
SHORT BROTHERS PLC Type/Model designation(s): SC7 Skyvan Series 3 aeroplanes

Certification Ref.: United Kingdom Airworthiness Ap proval Number 9877, Addendum 1

Foreign AD: Not applicable

Supersedure: None



### ATA 32 Landing Gear – Nose Landing Gear – Inspectio n

Manufacturer(s): Short Brothers PLC (formerly Short Brothers Ltd; Short Brothers & Harland Ltd.)

Applicability: SC7 Skyvan Series 3 aeroplanes, all variants, all serial numbers.

Reason: A fracture of the nose landing gear (NLG) s liding tube was reported. The subsequent investigation determined fatigue crackin g as possible cause of the failure.
This condition, if not detected and corrected, coul d lead to structural failure of the NLG, possibly resulting in loss of control of t he aeroplane during take-off or landing. To address this unsafe condition, the Messier-Dowty Ltd, the NLG manufacturer, issued Service Bulletin (SB) 32-17M t o provide inspection instructions. Consequently Short Brothers PLC issue d SB 32-74 which references Messier-Dowty Ltd SB 32-17M.
For the reasons described above, this AD requires o ne-time visual and fluorescent penetrant inspections and, depending on findings, accomplishment of applicable corrective action(s).

Effective Date: 26 November 2014EASA AD No.: 2014-0246

TE.CAP.00110-004 © European Aviation Safety Agency. All rights reserved. 2/2 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. Required Action(s) and Compliance Time(s): Required as indicated, unless accomplished previous ly: Note: Instructions provided by Messier-Dowty Ltd SB 32-17M are referenced in Short Brothers PLC SB 32-74. (1) Within 30 days after the effective date of this AD, accomplish a visual inspection of the NLG sliding tube in accordance wi th the instructions of paragraph 3.A of Messier-Dowty Ltd SB 32-17M. (2) Within 90 days after the effective date of this AD, accomplish a fluorescent penetrant inspection of the sliding tube in accorda nce with the instructions of paragraph 3.B of Messier-Dowty Ltd SB 32-17M. (3) If, during the inspection as required by paragr aph (1), or that required by paragraph (2) of this AD, as applicable, any crack is detected, before next flight, report the findings to Short Brothers PLC t o obtain approved repair instructions and accomplish the repair accordingly. (4) Within 30 days after accomplishment of each ins pection as required by paragraphs (1) and (2) of this AD, report the inspe ction results to Short Brothers PLC (see contact details in Remarks sectio n) by completing the Inspection Results Proforma in accordance with the instructions of paragraph 3.C.(2) of Messier-Dowty Ltd SB 32-17M. (5) From the effective date of this AD, installatio n of a sliding tube on an NLG or an NLG on an aeroplane, as applicable, is allowe d, provided that, before next flight after installation, the NLG sliding tub e passes the inspections in accordance with the instructions of paragraph 3 of Messier-Dowty Ltd SB 32-17M.

Ref. Publications: Short Brothers PLC SB 32-74 original issue dated 01 November 2014, Messier-Dowty Ltd SB 32-17M original issue dated 01 November 2014. 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

. 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: Airworthiness, Short Brothers PLC, P.O. Box 241, Ai rport Road, Belfast, BT3 9DZ Northern Ireland, United Kingdom; Telephone +44(0)2890462469; E-mail Michael.mulholland@aero.bombardier.com

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