EASA AD No : 2011-0097

EASA Form 110 Page 1/3 

## EASA AIRWORTHINESS DIRECTIVE

AD No.: 2011-0097

Date: 25 May 2011

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 participat e in the activities of EASA under Article 66 of that Regulation.
This AD is issued in accordance with EC 1702/2003, Part 21A.3B. In accordance with EC 2042/2003 Annex I, Part M.A.301, the continuing airworthiness of an aircra ft shall be ensured by accomplishing any applicable ADs. Consequently, no person may operate an aircraft to which an AD applies, except in accordance 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]. 

### Type Approval Holder’s Name :
BAE SYSTEMS (OPERATIONS) LTD Type/Model designation(s) :
BAe 146 and AVRO 146-RJ aeroplanes

TCDS Number: EASA.A.182

Foreign AD: Not applicable

Supersedure: None



### ATA 53 Fuselage – Nose Landing Gear Bay Left Hand Sidewall Stiffeners – Inspection / Repair

Manufacturer(s): BAE Systems (Operations) Ltd, British Aerospace pl c, British Aerospace (Commercial Aircraft) Ltd, British Aerospace (Operations) Ltd, British Aerospace Regional Aircraft Ltd, Brit ish Aerospace Regional Aircraft trading as Avro International Aerospace.

Applicability: BAe 146 and Avro 146-RJ aeroplane s, all models, all serial numbers, if a nose landing gear bay left hand sidewall with one of the following part numbers is installed: HC537L0002-000, -002 and -004, HC537H8021-000, -002 and -004 and HC537H8018-000.
Reason: During accomplishment of EASA AD 2007-0305 on an Avro 146-RJ85, a corner crack was found on the left hand Nose Landing Gear (NLG) sidewall well. The crack was located on one of the sidewall stiffeners adjacent to the area being inspected. In this instance, the cracking was severe enough to warrant replacement of the sidewall. A nalysis has shown that these types of cracks are likely to exist or develop in other aeroplanes of the same design. This condition, if not detected and correc ted, could result in failure of the sidewall and consequent in-flight rapi d decompression of the cabin and injury to its occupants. For the reasons described above, this AD requires repetitive inspections of the stiffeners on the left hand NLG sidew all. This AD also introduces an optional terminating action for the repetitive inspections.EASA AD No : 2011-0097

EASA Form 110 Page 2/3 Effective Date: 08 June 2011

Required action(s) and Compliance Time(s): Required as indicated, unless accomplished previously: (1) Before the aeroplane accumulates 12 000 flight cycles (FC) or within 4 000 FC after the effective date of this AD, whichever occurs later, and thereafter at intervals not to exceed 12 000 FC, perform a high frequency eddy current inspection of the st iffeners on the NLG gear bay left hand sidewall adjacent to the boss at the NLG retraction jack attachment pin hole in accordance with the instructions of paragraph 2.C. of the BAE Systems (Operations) Limited Inspection Service Bulletin (ISB) 53-229 Revision 1. (2) If, during the inspections required by paragraph (1) of this AD, any crack is found in the stiffeners, before next flight, contact BAE Systems (Operations) Ltd. for approved repair instructions and accomplish those instructions accordingly or, at the operator’s discretion, replace the NLG left hand bay sidewall with sidewall P/N HC537L0002-006 in accordance with the instructions of paragraph 2.G. of BAE Systems (Operations) Limited ISB.53-229 Revision 1. (3) Inspections and corrective actions accomplished before the effective date of this AD, in accordance with the instructions of BAE Systems (Operations) Ltd ISB.53-229 at origi nal issue, are considered acceptable for compliance with the requirements of this AD. (4) Replacement of the sidewall with sidewall P/N HC537L0002-006 on an aeroplane, in accordance with the in structions of paragraph 2.G. of the BAE Systems (Operations) Limited I SB.53-229 Revision 1 constitutes terminating action for the repetitive in spection requirements of this AD for that aeroplane.

Note: After replacement of the sidewall in accordance with the accomplishment instructions of paragraph 2.G. of the BAE Systems (Operations) Limited ISB.53-229 Revision 1, no further in spections are required until the airframe life limit, as defined in AMM 05-10-01, is reached and the aeroplane enters the Supplemental Structural Inspection Document programme. (5) After installation of a NLG gear bay left hand sidewall with sidewall with P/N HC537L0002-006 on an aeroplane, in accordance with the requirements of paragraph (2) of this AD or as specified in paragraph (4) of this AD, as applicable, do not install on an aeroplane a sidewall with one of the following Part Numbers on that aeroplane: HC537L0002-000, - 002 and -004, HC537H8021-000, -002 and -004 and HC537H8018-000.

Ref. Publications: BAE Systems (Operations) Limited In spection Service Bulletin ISB.53-229 Revision 1 dated 22 November 2010. The use of later approved revisions of this 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. This AD was posted on 18 April 2011 as PAD 11-041 for consultation until 16 May 2011. No comments were received during the consultation period. 3. Enquiries regarding this AD should be referred to the Airworthiness Directives, Safety Management & Re search Section, Certification Directorate, EASA. E-mail ADs@easa.europa.eu

.EASA AD No : 2011-0097

EASA Form 110 Page 3/3 4. For any question concerning the tec hnical content of the requirements in this AD, please contact: BAE Systems (Operations) Ltd, Cu stomer Information Department, Prestwick International Airport, Ay rshire, KA9 2RW, Scotland, United Kingdom; Telephone +44 1292 675207, Facsimile +44 1292 675704; E-mail: RApublications@baesystems.com

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