AD 2007-03-19

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

Before the accumulation of 2,500 total flight cycles on the MLGs, or within 250 flight cycles after August 13, 2004 (the effective date of AD 2004-14-16), whichever occurs later: Do a detailed inspection on the main fittings of the MLGs to detect discrepancies (i.e., linear paint cracks or lack of paint (paint peeling), any other paint damage, adhesion, paint bulging, or corrosion), in accordance with Part A of the Accomplishment Instructions of Bombardier Alert Service Bulletin (ASB) A601R-32-088, dated February 20, 2003; or Bombardier ASB 601R-32-088, Revision A, dated June 16, 2005, including Appendices, A, B, and C, dated February 20, 2003. Repeat the inspection thereafter at intervals not to exceed 100 flight cycles until paragraph (k) of this AD is accomplished.

Note 1: For the purposes of this AD, a detailed inspection is defined as: “An intensive visual examination of a specific structural area, system, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at intensity deemed appropriate by the inspector. Inspection aids such as mirror, magnifying lenses, etc., may be used. Surface cleaning and elaborate access procedures may be required.”

If any discrepancy is detected during any inspection required by paragraph (f) of this AD, before further flight: Do the related investigative/corrective actions in accordance with Part B or F of the Accomplishment Instructions of Bombardier ASB A601R-32-088, including Appendices A and C, dated February 20, 2003; or Bombardier ASB A601R-32-088, Revision A, dated June 16, 2005, including Appendices A, B, and C, dated February 20, 2003. If an eddy current inspection (a related investigative action specified in Part B) is used to confirm the detailed inspection findings, the next eddy current required by paragraph (h) of this AD must be conducted within 500 flight cycles after the eddy current inspection specified in this paragraph, and thereafter at intervals not to exceed 500 flight cycles until paragraph (k) of this AD is accomplished.

At the time specified in paragraph (f) of this AD, do an eddy current inspection on the main fittings of the MLGs to detect cracks, in accordance with Part B of the Accomplishment Instructions of Bombardier ASB A601R-32-088, including Appendix A, dated February 20, 2003; or Bombardier ASB A601R-32-088, Revision A, dated June 16, 2005, including Appendixes, A, B, and C, dated February 20, 2003. Repeat the eddy current inspection thereafter at intervals not to exceed 500 flight cycles, until paragraph (k) of this AD is accomplished. If any crack is found, before further flight, replace the affected main fittings of the MLGs with new or serviceable fittings in accordance with paragraph E.(5) of Part B of the Accomplishment Instructions of the service bulletin or in accordance with paragraph (k) of this AD. If any crack is found after the effective date of this AD, do the replacement in accordance with paragraph (k) of this AD.

(i) Before the accumulation of 2,500 total flight cycles on the MLGs, or within 500 flight cycles after August 13, 2004, whichever occurs later, service the shock strut of the MLGs in accordance with Part C or D, as applicable, of the Accomplishment Instructions of Bombardier ASB A601R-32-088, including Appendix B, dated February 20, 2003; or Bombardier ASB A601R-32-088, Revision A, dated June 16, 2005, including Appendices A, B, and C, dated February 20, 2003.

Within 500 flight cycles after completing the servicing required by paragraph (i) of this AD, inspect the shock strut of the MLGs for nitrogen pressure, visible chrome dimension, and oil leakage, in accordance with Part E of the Accomplishment Instructions of Bombardier ASB A601R-32-088, including Appendix B, dated February 20, 2003; or Bombardier ASB A601R-32-088, Revision A, dated June 16, 2005, including Appendices A, B, and C, dated February 20, 2003. Repeat the inspection thereafter at intervals not to exceed 500 flight cycles, until paragraph (k) of this AD is accomplished. If the nitrogen pressure and visible chrome dimensions are found outside the limits (the service bulletin refers to the airplane maintenance manual as the source of defined limits) and/or oil leakage is found, before further flight, service the affected shock strut of the MLGs in accordance with Part C or D, as applicable, of the Accomplishment Instructions of the service bulletin.

Within 39 months after the effective date of this AD: Replace the main fittings of the MLGs, P/Ns 601R85001-81 and 601R85001-82 (Messier Dowty Incorporated P/Ns 17064-105 and 17064-106), with new main fittings, P/Ns 601R85001-83 and 601R85001-84 (Messier Dowty Incorporated P/Ns 17064-107 and 17064-108), in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 601R-32-093, Revision B, dated July 14, 2005. Doing this replacement terminates all requirements of paragraphs (f), (g), (h), (i), and (j) of this AD.

Note 2: Bombardier Service Bulletin 601R-32-093, Revision B, refers to Messier-Dowty Service Bulletin M-DT SB17002-32-25, Revision 1, dated October 17, 2003, as an additional source of service information for replacing the main fittings.

As of the effective date of this AD, no person may install a main fitting of the MLG, P/Ns 601R85001-81 and 601R85001-82 (Messier Dowty Incorporated P/Ns 17064-105 and 17064-106), on any airplane.

Although the Accomplishment Instructions of Bombardier ASB A601R-32-088, dated February 20, 2003; and ASB 601R-32-088, Revision A, dated June 16, 2005; specify to report certain information to the manufacturer, this AD does not include that action.

Actions accomplished before the effective date of this AD in accordance with the service bulletins listed in Table 1 of this AD are acceptable for compliance with the actions in paragraph (k) of this AD.