EASA AD No.: 2012-0191R1

TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved. 1/3 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. 

## EASA AIRWORTHINESS DIRECTIVE

AD No.: 2012-0191R1

Date: 06 November 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 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 accor dance with the requirements of that AD, unless othe rwise specified by the Agency [EC 2042/2003 Annex I, Part M.A.303] or agreed with the Authority of the State of Registry [EC 216/200 8, 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

Revision: This AD revises EASA AD 2012-0191 dated 2 1 September 2012.



### ATA 05 Time Limits / Maintenance Checks – Nose Landing Gea r Main

Fitting Life Limitation – Implementation

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: Several occurrences of the aeroplane`s Nose Landing Gear (NLG) Main Fitting cracking have been reported. Subsequently in differ ent cases, NLG Main Fitting crack lead to collapsed NLG, locked NLG ste ering and an aeroplane`s un-commanded steering to the left. Cracks in the NLG Bell Housing are not detectable w ith the NLG fitted to the aeroplane and are difficult to detect during overha ul without substantial disassembly of the gear. This condition, if not corrected, could lead to deg radation of directional control on the ground or an un-commanded turn to the left a nd a consequent loss of control of the aeroplane on the ground, possibly re sulting in damage to the aeroplane and injury to occupants. Prompted by these findings, BAE Systems (Operations ) Ltd issued Inspection Service Bulletin (ISB) 32-186 (hereafter referred t o as the ISB) to introduce a new safe life of 16 000 flight cycles (FC) for cert ain NLG main fittings, having a Part Number (P/N) as identified in Paragraph 1A, ta bles 1, 2 and 3 of the ISB. To correct this unsafe condition, EASA issued AD 20 12-0191 to require implementation of the new safe-life limitation for the affected NLG main fittingsEASA AD No.: 2012-0191R1

TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved. 2/3 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. and replacement of fittings that have already excee ded the new limit. Since that AD was issued, it was found that clarifi cation is necessary regarding the existing NLG main fitting life limits. Conseque ntly, this AD is revised by adding a Note to clarify that the current life limi ts, as specified in the applicable Aircraft Maintenance Manual (AMM), remain valid and should be applied, pending compliance with this AD.

Effective Date: Revision 1: 20 November 2012 Original issue: 05 October 2012

Required Action(s) and Compliance Time(s): Required as indicated, unless accomplished previous ly: (1) Within the compliance time as specified in Tabl e 1 of this AD, as applicable, and thereafter, at intervals not to exc eed 16 000 FC, replace each affected NLG main fitting, having a P/N as ide ntified in Paragraph 1A, tables 1, 2 and 3 of the ISB, in accordance wit h the accomplishment instruction of the ISB.

Table 1 – Replacement thresholds FC accumulated by the NLG Main Fitting since first installation on an aeroplane Compliance Time

Equal to or more than 29 000 FC Within 12 months after 05 October 2012 [the effective date of the original issue of this AD] Equal to or more than 20 000 FC but less than 29 000 FC Within 24 months after 05 October 2012 [the effective date of the original issue of this AD]

Equal to or more than 16 000 FC but less than 20 000 FC Within 36 months after 05 October 2012 [the effective date of the original issue of this AD]

Less than 16 000 FC Before accumulating 16 000 FC o r within 36 months after 05 October 2012 [the effective date of the original issue of this AD], whichever occurs later.
Note: During the compliance time allowed by this AD , the existing NLG main fitting life limits as specified in the applicable AMM Chapter 5, which is also subject to an EASA AD, are still valid and should n ot be exceeded. (2) From 05 October 2012 [the effective date of the original issue of this AD], do not install a NLG main fitting, having a P/N as identified in Paragraph 1A, tables 1, 2 and 3 of the ISB, on an aeroplane, unless in compliance with the requirements of this AD. (3) Compliance with the requirements of paragraphs (1) and (2) of this AD can be demonstrated by: (3.1) Revising as follows, the approved Aircraft Ma intenance Programme (AMP) on the basis of which the operator or the own er ensures the continuing airworthiness of each operated aeroplane : Incorporate the NLG Main Fitting life limitation a s specified in the ISB,
and (3.2) Complying with the approved AMP as described in paragraph (3.1) of this AD.EASA AD No.: 2012-0191R1

TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved. 3/3 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. Ref. Publications: BAE Systems (Operations) Ltd ISB.32-186 initial iss ue dated 12 April 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. The original issue of this AD was posted on 14 A ugust 2012 as PAD 12- 108 for consultation until 11 September 2012. The C omment Response Document can be found at http://ad.easa.europa.eu

. 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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