AD 2010-10-22

(a) This AD becomes effective June 25, 2010.

(b) This AD supersedes AD 2005-23-12, Amendment 39-14370.

(c) This AD applies to all BAE SYSTEMS (Operations) Limited Model BAe 146-100A, -200A, and -300A series airplanes; and Model Avro 146-RJ70A, 146-RJ85A, and 146-RJ100A airplanes; certificated in any category.

Note 1:

This AD requires revisions to certain operator maintenance documents to include new inspections. Compliance with these inspections is required by 14 CFR 91.403(c). For airplanes that have been previously modified, altered, or repaired in the areas addressed by these inspections, the operator may not be able to accomplish the inspections described in the revisions. In this situation, to comply with 14 CFR 91.403(c), the operator must request approval for an alternative method of compliance (AMOC) according to paragraph (k) of this AD. The request should include a description of changes to the required inspections that will ensure the continued operational safety of the airplane.

(d) Air Transport Association (ATA) of America Code 05.

(e) This AD results from issuance of a later revision to the airworthiness limitations of the BAE SYSTEMS (Operations) Limited BAe146 Series/Avro146-RJ Series Aircraft Maintenance Manual (AMM), which specifies new inspections and compliance times for inspection and replacement actions. We are issuing this AD to ensure that fatigue cracking of certain structural elements is detected and corrected, and to prevent ignition sources in the fuel tanks; fatigue cracking of certain structural elements could adversely affect the structural integrity of these airplanes.

(f) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.

(g) Within 30 days after December 27, 2005 (the effective date of AD 2005-23-12), revise the Airworthiness Limitations Section (ALS) of the Instructions for Continued Airworthiness to incorporate new and more restrictive life limits for certain items and new and more restrictive inspections to detect fatigue cracking in certain structures, in accordance with a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the Civil Aviation Authority (or its delegated agent).

(h) Within 90 days after the effective date of this AD, revise Chapter 5 of the BAE SYSTEMS (Operations) Limited BAe146 Series/Avro146-RJ Series AMM to incorporate new and more restrictive life limits for certain items and new and more restrictive inspections to detect fatigue cracking in certain structures, and to add fuel system critical design configuration control limitations (CDCCLs) to prevent ignition sources in the fuel tanks, in accordance with a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA) (or its delegated agent). Incorporating the new and more restrictive life limits and inspections into the ALS terminates the requirements of paragraph (g) of this AD, and after incorporation has been done, the limitations required by paragraph (g) of this AD may be removed from the ALS.

Note 2:

Guidance on revising Chapter 5 of the BAE SYSTEMS (Operations) Limited BAe146 Series/Avro146-RJ Series AMM, Revision 97, dated July 15, 2009, can be found in the applicable sub-chapters listed in Table 1 of this AD.

Note 3:

Sub-chapter 05-15-00 of the BAE SYSTEMS (Operations) Limited BAe146 Series/Avro146-RJ Series AMM, is the CDCCL.

Note 4:

Within Sub-chapter 05-20-00 of the BAE SYSTEMS (Operations) Limited BAe146 Series/Avro146-RJ Series AMM, the relevant issues of the support documents are as follows: BAE SYSTEMS (Operations) Limited BAe 146 Series/Avro 146-RJ Corrosion Prevention and Control Program Document CPCP-146-01, Revision 3, dated July 15, 2008, including BAE SYSTEMS (Operations) Limited Temporary Revision (TR) 2.1, dated December 2008; and BAE SYSTEMS (Operations) Limited BAe146 Series Supplemental Structural Inspection Document SSID-146-01, Revision 1, dated June 15, 2009.

Note 5:

Within Sub-chapter 05-20-01 of the BAE SYSTEMS (Operations) Limited BAe146 Series/Avro146-RJ Series AMM, the relevant issue of BAE SYSTEMS (Operations) Limited BAe 146/Avro 146-RJ Maintenance Review Board Report Document MRB 146-01, Issue 2, is Revision 15, dated March 2009 (mis-identified in EASA AD 2009-0215, dated October 7, 2009, as being dated May 2009).

Note 6:

Notwithstanding any other maintenance or operational requirements, components that have been identified as airworthy or installed on the affected airplanes before the revision of the ALS, as required by paragraph (g) of this AD; or before revision of Chapter 5 of the AMM, as required by paragraph (h) of this AD; do not need to be reworked in accordance with the CDCCLs. However, once the ALS or AMM has been revised, future maintenance actions on these components must be done in accordance with the CDCCLs.

(i) Except as specified in paragraph (k) of this AD: After the actions specified in paragraph (g) or (h) of this AD have been accomplished, no alternative inspections or inspection intervals may be approved for the structural elements specified in the documents listed in paragraph (g) or (h) of this AD.

(j) Modifying the main fittings of the main landing gear in accordance with Messier-Dowty Service Bulletin 146-32-171, dated August 11, 2009, extends the safe limit of the main landing gear main fitting from 32,000 landings to 50,000 landings on the main fitting.

(k) The Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to ATTN: Todd Thompson, Aerospace Engineer, International Branch, ANM-116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98057-4056; telephone (425) 227-1175; fax (425) 227-1149. Before using any approved AMOC on any airplane to which the AMOC applies, notify your principal maintenance inspector (PMI) or principal avionics inspector (PAI), as appropriate, or lacking a principal inspector, your local Flight Standards District Office. The AMOC approval letter must specifically reference this AD.

(l) EASA Airworthiness Directive 2009-0215, dated October 7, 2009; and Messier-Dowty Service Bulletin 146-32-171, dated August 11, 2009; also address the subject of this AD.

(m) If you do the optional modification specified in this AD, you must use Messier-Dowty Service Bulletin 146-32-171, dated August 11, 2009, to do those actions, unless the AD specifies otherwise.

(1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51.

(2) For Messier-Dowty service information identified in this AD, contact Messier-Dowty Limited, Cheltenham Road, Gloucester GL2 9QH, England; telephone +44(0)1452 712424; fax +44(0)1452 713821; Internet https://techpubs.services.messier-dowty.com.

(3) You may review copies of the service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington. For information on the availability of this material at the FAA, call 425-227-1221.

(4) You may also review copies of the service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.