EASA AD No.: 2012-0136

CAP.00110-001 © European Aviation Safety Agency. Al l 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.: 2012-0136

Date: 20 July 2012

Note: This Airworthiness Directive (AD) is issued b y EASA, acting in accordance with Regulation (EC) No 216/2008 on behalf of the Europe an Community, its Member States and of the European third countries that participate in th e 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 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) :
BAe 146 and AVRO 146-RJ aeroplanes

TCDS Number: EASA.A.182

Foreign AD: Not applicable

Supersedure: None



### ATA 57 Wings – Forward Engine Pylon Pick-up Brackets – Ins pection / Repair

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

Applicability: BAe 146 and AVRO 146-RJ aeroplanes, all models, all serial numbers.

Reason: While carrying out a scheduled environmenta l inspection, an operator found a cracked number 1 engine forward outboard pylon pick -up bracket. Cracks were present on the upper flange of the bracket running between all 3 attachment bolt holes. Subsequent investigation revealed that the cause of cracking was stress corrosion. Cracking of the pylon pick-up bra ckets at the top and bottom flanges could reduce the capability of the brackets to support the ultimate sideload, particularly if cracking is present on more t han one flange.
This condition, if not detected and corrected, coul d result in the engine pylon separation from the wing, likely resulting in damag e to the aeroplane and possible injury to persons on the ground. To address this concern, BAE Systems (Operations) L imited published Inspection Service Bulletin (ISB) 57-073, currently at Revision 1.
For reasons described above, this AD requires the i nspection and, depending on findings, repair of the affected pylon pick-up b rackets.

Effective Date: 03 August 2012EASA AD No.: 2012-0136

CAP.00110-001 © European Aviation Safety Agency. Al l 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) Initially within the compliance time as specifi ed in Table 1 of this AD, as applicable, and thereafter at intervals not to exc eed 24 months, inspect the flanges of the Rib 10 forward pylon pick up bra cket of each engine pylon, in accordance with the instructions of parag raph 2C of BAE Systems(Operations) Limited ISB 57-073 Revision 1.

Table 1

Engine Pylon Configuration Compliance time, after t he effective date of this AD

No forward pylon pick-up bracket replaced since first flight of the aeroplane 6 months

Forward pylon pick-up bracket replaced 20 months

(2) If, during any inspection as required by paragr aph (1) of this AD, any cracking, corrosion or other defects of a Rib 10 fo rward pylon pick up bracket are detected, before next flight, accomplis h a repair in accordance with the instructions of paragraph 2C of BAE System s(Operations) Limited ISB 57-073 Revision 1. (3) Inspection and correction of an aeroplane, befo re the effective date of this AD, in accordance with the instructions of ISB 57-0 73 at initial issue constitutes an acceptable method of compliance with initial requirements of paragraphs (1) and (2) of this AD. After the effect ive date of this AD ISB 57-073 at Revision 1 has to be used. (4) Repair of a Rib 10 forward pylon pick up bracke t, as required by paragraph (2) of this AD, does not constitute terminating act ion for the repetitive inspections required by paragraph (1) of this AD.

Ref. Publications: BAE Systems (Operations) Limited ISB 57-073 at Revi sion 1 dated 27 January 2012. 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 14 June 2012 as PAD 12-063 for consultation until 12 July 2012. No comments were received during the consultation period. 3. Enquiries regarding this PAD should be referred to 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, United Kingdom; Telephone: +44 1292 675207, Fax: +44 1292 675704; E-mail: RApublications@baesystems.com

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