EASA AD No.: 2013-0206

TE.CAP.00110-003 © 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.: 2013-0206

Date: 09 September 2013

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: BAE SYSTEMS (OPERATIONS) LTD Type/Model designation(s):
Jetstream Series 3100 and 3200 aeroplanes

TCDS Number: EASA.A.191

Foreign AD: Not applicable

Supersedure: None



### ATA 32 Landing Gear – Main Landing Gear – Modificat ion

Manufacturer(s): British Aerospace PLC, British Aer ospace (Commercial Aircraft) Ltd, British Aerospace Regional Aircraft Ltd, Jetstream Aircraft Ltd and British Aerospace (Operations) Ltd.

Applicability: Jetstream Series 3100 and 3200 aerop lanes, all models, all serial numbers.

Reason: An occurrence of Jetstream 3100 main landin g gear (MLG) failure after landing was reported. The subsequent investigation revealed stress corrosion cracking of the MLG yoke pintle housing as a root cause of t he MLG failure. Degradation of the surface protection by abrasion can occur whe n the forward face of the yoke pintle rotates against the pintle bearing, whi ch introduces corrosion pits and, consequently, stress corrosion cracking.
This condition, if not corrected, could lead to str uctural failure of the MLG possibly resulting in loss of control of the aeropl ane during take-off or landing

runs. To address this potential unsafe condition, BAE Sys tems (Operations) Ltd issued Service Bulletin (SB) 32-JM7862 to provide i nstruction for installation of a protective washer fitted at the forward spigot on both, left hand (LH) and right hand (RH), MLG. For the reasons described above, this AD requires i nstallation of a washer to protect the MLG at the forward face of the yoke pin tle.

Effective Date: 23 September 2013EASA AD No.: 2013-0206

TE.CAP.00110-003 © 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: (1) Within the compliance time, as specified in par agraph 1.N of BAE Systems (Operations) Ltd SB 32-JM7862, modify the LH and RH MLG installation at the forward spigot in accordance with the accomplis hment instruction of BAE Systems (Operations) Ltd SB 32-JM7862 revision 1. (2) Modification of an MLG, before the effective da te of this AD, in accordance with BAE Systems (Operations) Ltd SB 32-JM7862 at i nitial issue, is acceptable to comply with the requirements of parag raph (1) of this AD. (3) From the effective date of this AD, installatio n of a replacement LH or RH MLG on an aeroplane is allowed only if it is in com pliance with the requirements of paragraph (1) or (2) of this AD.

Ref. Publications: BAE Systems (Operations) Ltd SB 32-JM7862 original issue, dated 08 April 2013 or revision 1, dated 07 May 2013. The use of later approved revisions of this documen t 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. This AD was posted on 29 July 2013 as PAD 13-109 for consultation until 26 August 2013. No comments were received during th e consultation period. 3. Enquiries regarding this AD should be referred t o the Safety Information Section, Executive 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: BAE Systems (Operations) Ltd, Customer Information Department, Prestwick International Airport, Ayrshire, KA9 2RW, Scotland, The United Kingdom; Telephone +44 1292 675207, Facsimile +44 1 292 675704; E-mail: RApublications@baesystems.com

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