Airworthiness Directive · Amendment 39-16301 · BAE SYSTEMS (Operations) Limited Model BAe 146 Airplanes and Model Avro 146-RJ Airplanes
BAE SYSTEMS (Operations) Limited Model BAe 146 Airplanes and Model Avro 146-RJ Airplanes
Superseded. A later AD replaced this one: AD 2011-24-06. Comply with the one in force.
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.
The FAA is superseding an existing airworthiness directive (AD), which applies to Model BAe 146 airplanes and Model Avro 146-RJ airplanes. That AD currently requires revising the Airworthiness Limitations Section (ALS) of the Instructions for Continued Airworthiness to incorporate life limits for certain items and inspections to detect fatigue cracking in certain structures. This new AD requires incorporating new and more restrictive life limits for certain items and for certain inspections to detect fatigue cracking in certain structures. This AD also requires revising the airworthiness limitations to include critical design configuration control limitations for the fuel system. This AD results from issuance of a later revision to the airworthiness limitations. 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.
You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.
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).
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.
| AMM Sub-chapter | Subject |
|---|---|
| 05-10-01 | Airframe Airworthiness Limitations before Life Extension Programme. |
| 05-10-05 1 | Airframe Airworthiness Limitations, Life Extension Programme Landings Life Extended. |
| 05-10-10 2 | Airframe Airworthiness Limitations, Life Extension Programme Calendar Life Extended. |
| 05-10-15 | Aircraft Equipment Airworthiness Limitations. |
| 05-10-17 | Power Plant Airworthiness Limitations. |
| 05-15-00 | Critical Design Configuration Control Limitations (CDCCL)—Fuel System Description and Operation. |
| 05-20-00 3 | Scheduled Maintenance. |
| 05-20-01 | Airframe Scheduled Maintenance—Before Life Extension Programme. |
| 05-20-05 1 | Airframe Scheduled Maintenance—Life Extension Programme Landings Life Extended. |
| 05-20-10 2 | Airframe Scheduled Maintenance—Life Extension Programme Calendar Life Extended. |
| 05-20-15 | Aircraft Equipment Scheduled Maintenance. |
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.
