Airworthiness Directive · Amendment 39-15137 · BAE Systems (Operations) Limited Model ATP Airplanes
BAE Systems (Operations) Limited Model ATP Airplanes
Superseded. A later AD replaced this one: AD 2010-05-05. Comply with the one in force.
This AD applies to all BAE Systems (Operations) Limited Model ATP airplanes, certificated in any category.
Note 1: This AD requires revisions to certain operator maintenance documents to include new and revised 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 according to paragraph (m) of this AD. The request should include a description of changes to the required inspections that will ensure the continued damage tolerance of the affected structure. The FAA has provided guidance for this determination in Advisory Circular (AC) 25-1529.
The FAA is superseding an existing airworthiness directive (AD), which applies to all BAE Systems (Operations) Limited Model ATP airplanes. The existing AD currently requires revising the Airworthiness Limitations Section (ALS) of the Instructions for Continued Airworthiness (ICA) to incorporate life limits for certain items and inspections to detect fatigue cracking in certain structures; to incorporate new inspections to detect fatigue cracking of certain significant structural items (SSIs); and to revise life limits for certain equipment and various components. This new AD requires revising the ALS of the ICA to include revised requirements. This AD results from the determination that additional and revised inspections of the fuselage are needed. We are issuing this AD to detect and correct fatigue cracking of certain structural elements, which could result in reduced structural integrity of the airplane and consequent rapid decompression of the airplane.
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Within 30 days after February 7, 2001 (the effective date of AD 2000-26-10, amendment 39-12060, which was superseded by AD 2005-19-03), revise the Airworthiness Limitations section (ALS) of the Instructions for Continued Airworthiness according to a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA. One approved method is by incorporating Section 05-00-00, dated August 15, 1997, of the British Aerospace ATP Aircraft Maintenance Manual (AMM), dated October 15, 1999, into the ALS. This section references other chapters of the AMM. The applicable revision level of the referenced chapters is that in effect on February 7, 2001. Doing the revision specified in paragraph (g) of this AD replaces Chapters 27, 32, 53, and 54 listed in Section 05-10-11 and Chapters 52, 53, 54, 55, and 57 listed in Section 05-10-17 that are in effect on February 7, 2001, with Chapters 27, 32, 53, and 54 listed in Section 05-10-11, “Mandatory Life Limitations (Airframe)”; and Chapters 52, 53, 54, 55, and 57 listed in Section 05-10-17, “Structurally Significant Items (SSIs)”; both dated July 15, 2004; of the British Aerospace ATP AMM. Doing the revision specified in paragraph (k) of this AD replaces Sections 05-10-12, 05-10-15, and 05-10-17 with the corresponding sections specified in paragraph (k) of this AD.
Within 30 days after September 28, 2005 (the effective date of AD 2005-19-03, amendment 39-14268, which was superseded by AD 2006-18-09), revise the ALS of the Instructions for Continued Airworthiness according to a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA. One approved method is by incorporating the tasks for Chapters 27, 32, 53, and 54 listed in Section 05-10-11, “Mandatory Life Limitations (Airframe)”; and the tasks for Chapters 52, 53, 54, 55, and 57 listed in Section 05-10-17, “Structurally Significant Items (SSIs)”; both dated July 15, 2004; of the British Aerospace ATP AMM; into the ALS. These chapters replace the corresponding chapters in Section 05-00-00, dated August 15, 1997, of the British Aerospace ATP AMM as specified in paragraph (f) of this AD. Doing the revision specified in paragraph (h) of this AD replaces certain Chapter 52 and 53 tasks listed in Section 05-10-17, “Structurally Significant Items (SSIs),” dated July 15, 2004, of the British Aerospace ATP AMM, with the corresponding Chapter 52 and 53 tasks listed in BAE Systems (Operations) Limited Service Bulletin ATP-51-002, dated December 20, 2005. Doing the revision specified in paragraph (k) of this AD replaces Chapters 52, 53, 54, 55, and 57 listed in Section 05-10-17 with the corresponding Section 05-10-17 specified in paragraph (k) of this AD.
Within 30 days after September 21, 2006 (the effective date of AD 2006-18-09), revise the ALS of the Instructions for Continued Airworthiness by incorporating the new and revised tasks for Chapters 52 and 53 as specified in BAE Systems (Operations) Limited Service Bulletin ATP-51-002, dated December 20, 2005, into the ALS. The revised Chapter 52 and 53 tasks replace the corresponding Chapter 52 and 53 tasks in Section 05-10-17, “Structurally Significant Items (SSIs),” dated July 15, 2004, of the British Aerospace ATP AMM, as specified in paragraph (g) of this AD.
(i) Except as provided by paragraph (m) of this AD: After the actions specified in paragraphs (f), (g), and (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 paragraphs (f), (g), and (h) of this AD.
Although BAE Systems (Operations) Limited Service Bulletin ATP-51-002, dated December 20, 2005, specifies to submit certain information to the manufacturer, this AD does not include that requirement.
Within 30 days after the effective date of this AD, revise the ALS of the Instructions for Continued Airworthiness according to a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA. One approved method is by incorporating Section 05-10-12, “Mandatory Life Limitations (Airframe—Structures),” dated January 15, 2007; Section 05-10-15, “Mandatory Life Limitations (Powerplant/Engine/APU—Structures),” dated January 15, 2007; and Section 05-10-17, “Structurally Significant Items (SSIs),” dated January 15, 2007; of the BAE Systems (Operations) Limited ATP AMM; into the ALS. The revised sections replace the corresponding sections specified in paragraphs (f) and (g) of this AD.
(l) Except as provided by paragraph (m) of this AD: After the action specified in paragraph (k) of this AD has been accomplished, no alternative inspections or inspection intervals may be approved for the structural elements specified in the documents listed in paragraph (k) of this AD.
