EASA AD No : 2012-0003

EASA Form 110 Page 1/2 

## EASA AIRWORTHINESS DIRECTIVE

AD No.: 2012-0003

Date: 06 January 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 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 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]. 

### 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 30 Ice and Rain Protection – Wing Leading Edge Anti-Ic ing Piccolo Tube End Cap – Inspection

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 series aerop lanes, all models, all serial numbers.

Reason: An operator reported the loss of the wing l eading edge anti-icing piccolo tube end caps on two aircraft. This was discovered duri ng routine zonal inspections when the wing tips were removed. The lo ss of the end cap would result in a reduction in anti-icing efficiency, ove r the outboard portion of the leading edge of that wing, affecting approximately 25% of the wingspan towards the wing tip. The System Safety Analysis (SSA) classifies the los s of anti-icing of both of the outer wings as hazardous if the loss is not ind icated to the crew. The loss of a piccolo tube end cap would not be indicated to the flight crew and, therefore, this reduction in anti-icing capability on one wing must also be classified as hazardous. This condition, if not detected and corrected, coul d result in ice accretion on the wing leading edge, or run-back ice and could le ad to a reduction in the stall margin on approach together with a reduction in roll control authority. For the reasons described above, this AD requires a one-off inspection of the piccolo tube end caps. The results of this inspect ion will be used to establish a suitable repeat inspection period, which will be introduced through the Maintenance Review Board (MRB) process.

Effective Date: 20 January 2012EASA AD No : 2012-0003

EASA Form 110 Page 2/2 Required Action(s) and Compliance Time(s): Required as indicated, unless accomplished previous ly: (1) Within 12 months after the effective date of th is AD, inspect the anti-icing piccolo tube end caps in accordance with paragraph 2.C of BAE Systems (Operations) Ltd Inspection Service Bulleti n (ISB).30-025 at Initial Issue. (2) If, during the inspection as required by paragr aph (1) of this AD, a lost or damaged anti-icing piccolo tube end cap is detected , before next flight, replace the tube assembly or repair it in accordanc e with an approved repair scheme. (3) Within 14 days after accomplishment of the insp ection as required by paragraph (1) of this AD, submit a report of findin gs to BAE Systems (Operations) Ltd, in accordance with the instructio ns of paragraph 2.F of the ISB.30-025, using the inspection report form in the Appendix 1 of BAE Systems (Operations) Ltd ISB.30-025.

Ref. Publications: BAE Systems (Operations) Limited Inspection Service Bulletin ISB.30-025 at Initial Issue, dated 19 April 2011. 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 November 2011 as PAD 11 -127 for consultation until 27 December 2011. No comments we re received during the 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 1292 67570 4, E-mail: RApublications@baesystems.com

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