Airworthiness Directive · Amendment 39-16661 · Fuselage
BAE SYSTEMS (OPERATIONS) LIMITED Model BAe 146 Airplanes, and Model Avro 146-RJ Airplanes
This AD applies to all BAE SYSTEMS (OPERATIONS) LIMITED Model BAe 146-100A, −200A, and −300A airplanes; and Model Avro 146-RJ70A, 146-RJ85A, and 146-RJ100A airplanes; certificated in any category.
We are superseding an existing airworthiness directive (AD) that applies to the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as:
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 the applicable compliance time specified in paragraph (g)(1) or (g)(2) of this AD, perform an external eddy current inspection of the forward fuselage skin to detect cracking, in accordance with the Accomplishment Instructions of BAE Systems (Operations) Limited Modification Service Bulletin ISB.53-167, including Appendix 2, Revision 1, dated May 18, 2004. Doing the inspection required by paragraph (j) of this AD terminates the requirements of this paragraph of this AD.
(1) For Model BAe 146 series airplanes: Inspect before the accumulation of 16,000 total landings, or within 4,000 landings after the August 2, 2005 (the effective date of AD 2005-13-19), whichever is later.
(i) For areas where no crack is found, repeat the inspection at intervals not to exceed 8,000 landings.
(ii) For areas where any crack is found, before further flight, perform repairs in accordance with a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA, the Civil Aviation Authority (CAA) (or its delegated agent), or EASA (or its delegated agent). No further inspection of any repaired area is required by paragraph (g) of this AD.
(2) For Model Avro 146-RJ series airplanes: Inspect before the accumulation of 10,000 total landings, or within 2,000 landings after August 2, 2005, whichever is later.
(i) For areas where no crack is found, repeat the inspection at intervals not to exceed 4,000 landings.
(ii) For areas where any crack is found, before further flight, perform repairs in accordance with a method approved by the Manager, International Branch, ANM-116, the CAA (or its delegated agent), or EASA (or its delegated agent). No further inspection of any repaired area is required by paragraph (g) of this AD.
Inspections accomplished before August 2, 2005, in accordance with BAE Systems (Operations) Limited Inspection Service Bulletin ISB.53-167, including Appendices 2 and 3, all dated June 27, 2003, are considered acceptable for compliance with the corresponding action specified in paragraph (g) of this AD.
(i) Although BAE Systems (Operations) Limited Modification Service Bulletin ISB.53-167, including Appendix 2, Revision 1, dated May 18, 2004, specifies to submit Appendix 1 of that service bulletin with certain information to the manufacturer, this AD does not include that requirement.
For Model BAe 146 airplanes: At the latest of the times specified in paragraphs (j)(1), (j)(2), and (j)(3) of this AD, do an external eddy current inspection of the forward fuselage skin to detect cracking, in accordance with the Accomplishment Instructions of BAE Systems (Operations) Limited Inspection Service Bulletin ISB.53-167, including Appendix 2, Revision 4, dated June 10, 2010. Repeat the inspection thereafter at intervals not to exceed 3,600 flight cycles for areas specified in Drawings 2, 3, 4, 5, and 7 of BAE Systems (Operations) Limited Inspection Service Bulletin ISB.53-167, including Appendix 2, Revision 4, dated June 10, 2010, and at intervals not to exceed 4,600 flight cycles for areas specified in Drawings 1, 6, 8, and 9 of BAE Systems (Operations) Limited Inspection Service Bulletin ISB.53-167, including Appendix 2, Revision 4, dated June 10, 2010. Doing the inspection required by this paragraph terminates the requirements of paragraph (g) of this AD for that airplane.
(1) Before the accumulation of 16,000 total flight cycles.
(2) Within 2,000 flight cycles after the effective date of this AD.
(3) Within the applicable times specified in paragraphs (j)(3)(i) and (j)(3)(ii) of this AD.
(i) For areas specified in Drawings 2, 3, 4, 5, and 7 of BAE Systems (Operations) Limited Inspection Service Bulletin ISB.53-167, including Appendix 2, Revision 4, dated June 10, 2010: Within 3,600 flight cycles after the last inspection done in accordance with paragraph (g) of this AD.
(ii) For areas specified in Drawings 1, 6, 8, and 9 of BAE Systems (Operations) Limited Inspection Service Bulletin ISB.53-167, including Appendix 2, Revision 4, dated June 10, 2010: Within 4,600 flight cycles after the last inspection done in accordance with paragraph (g) of this AD.
(k) For Model Avro 146-RJ airplanes: At the latest of the times specified in paragraph (k)(1), (k)(2), and (k)(3) of this AD, do an external eddy current inspection of the forward fuselage skin to detect cracking, in accordance with the Accomplishment Instructions of BAE Systems (Operations) Limited Inspection Service Bulletin ISB.53-167, including Appendix 2, Revision 4, dated June 10, 2010. Repeat the inspection thereafter at intervals not to exceed 2,400 flight cycles for areas specified in Drawings 2, 3, 4, 5, and 7 of BAE Systems (Operations) Limited Inspection Service Bulletin ISB.53-167, including Appendix 2, Revision 4, dated June 10, 2010, and 3,000 flight cycles for areas specified in Drawings 1, 6, 8, and 9 of BAE Systems (Operations) Limited Inspection Service Bulletin ISB.53-167, including Appendix 2, Revision 4, dated June 10, 2010. Doing the inspection required by this paragraph terminates the requirements of paragraph (g) of this AD for that airplane.
(1) Before the accumulation of 10,000 total flight cycles.
(2) Within 1,000 flight cycles after the effective date of this AD.
(3) Within the applicable times specified in paragraphs (k)(3)(i) and (k)(3)(ii) of this AD.
(i) For areas specified in Drawings 2, 3, 4, 5, and 7 of BAE Systems (Operations) Limited Inspection Service Bulletin ISB.53-167, including Appendix 2, Revision 4, dated June 10, 2010: Within 3,600 flight cycles after the last inspection done in accordance with paragraph (g) of this AD.
(ii) For areas specified in Drawings 1, 6, 8, and 9 of BAE Systems (Operations) Limited Inspection Service Bulletin ISB.53-167, including Appendix 2, Revision 4, dated June 10, 2010: Within 4,600 flight cycles after the last inspection done in accordance with paragraph (g) of this AD.
(l) If any cracking is found during any inspection required by paragraph (j) or (k) of this AD, before further flight, accomplish the repair in accordance with a method approved by the FAA or EASA (or its delegated agent). Repair of an airplane in accordance with the requirements of this paragraph of this AD does not constitute terminating action for the inspection requirements of this AD.
Inspections done before the effective date of this AD in accordance with BAE Systems (Operations) Limited Inspection Service Bulletin ISB.53-167, including Appendix 2, Revision 2, dated November 17, 2008; or Revision 3, dated June 17, 2009; are acceptable for compliance with the corresponding requirements of paragraphs (j) and (k) of this AD.
Note 1: This AD differs from the MCAI and/or service information as follows: No differences.
