EASA AD No.: 2012-0136 

CAP.00110-001 © 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.: 2012-0136 

Date: 20 July 2012 

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 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 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]. 

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 – Inspection / 

Repair 

Manufacturer(s): BAE Systems (Operations) Ltd, British Aerospace plc, British Aerospace 

(Commercial Aircraft) Ltd, British Aerospace (Operations) 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 environmental 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 brackets 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 than one flange. 

This condition, if not detected and corrected, could result in the engine pylon 

separation from the wing, likely resulting in damage to the aeroplane and 

possible injury to persons on the ground. 

To address this concern, BAE Systems (Operations) Limited published 

Inspection Service Bulletin (ISB) 57-073, currently at Revision 1. 

For reasons described above, this AD requires the inspection and, depending 

on findings, repair of the affected pylon pick-up brackets. 

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

CAP.00110-001 © European Aviation Safety Agency. All rights reserved. 2/2 

Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.

Required Action(s) 

and Compliance 

Time(s): 

Required as indicated, unless accomplished previously:

(1) Initially within the compliance time as specified in Table 1 of this AD, as 

applicable, and thereafter at intervals not to exceed 24 months, inspect 

the flanges of the Rib 10 forward pylon pick up bracket of each engine 

pylon, in accordance with the instructions of paragraph 2C of BAE 

Systems(Operations) Limited ISB 57-073 Revision 1. 

Table 1 

Engine Pylon Configuration Compliance time, after the 

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 paragraph (1) of this AD, any 

cracking, corrosion or other defects of a Rib 10 forward pylon pick up 

bracket are detected, before next flight, accomplish a repair in accordance 

with the instructions of paragraph 2C of BAE Systems(Operations) Limited 

ISB 57-073 Revision 1. 

(3) Inspection and correction of an aeroplane, before the effective date of this 

AD, in accordance with the instructions of ISB 57-073 at initial issue 

constitutes an acceptable method of compliance with initial requirements of 

paragraphs (1) and (2) of this AD. After the effective date of this AD ISB 

57-073 at Revision 1 has to be used. 

(4) Repair of a Rib 10 forward pylon pick up bracket, as required by paragraph 

(2) of this AD, does not constitute terminating action for the repetitive 

inspections required by paragraph (1) of this AD. 

Ref. Publications: BAE Systems (Operations) Limited ISB 57-073 at Revision 1 dated 27 January 

2012. 

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 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 content 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.