Airworthiness Directive · Amendment 39-18491 · Wings
Bombardier, Inc. Airplanes
This AD applies to Bombardier, Inc. Model CL-600-2B16 airplanes, certificated in any category, serial numbers 5301 through 5665 inclusive, and 5701 through 5920 inclusive.
We are superseding Airworthiness Directive (AD) 2014-17-51 for certain Bombardier, Inc. Model CL-600-2B16 airplanes. AD 2014-17-51 required inspecting the inboard flap fasteners of the hinge-box forward fitting at Wing Station (WS) 76.50 and WS 127.25 to determine the orientation and condition of the fasteners, as applicable, and replacement or repetitive inspections of the fasteners if necessary. AD 2014-17-51 also provided for optional terminating action for the requirements of that AD. This new AD requires accomplishment of the previously optional terminating action. This AD was prompted by a determination that that additional action is necessary. We are issuing this AD to detect and correct incorrectly oriented or fractured fasteners, that could result in premature failure of the fasteners attaching the inboard flap hinge-box forward fitting; failure of the fasteners could lead to the detachment of the flap hinge box and the flap surface, and consequent loss of control of the airplane.
This paragraph restates the requirements of paragraph (g) of AD 2014-17-51, with new service information. For airplanes on which the actions required by AD 2014-03-17 have not been done as of November 12, 2014 (the effective date of AD 2014-17-51): Within 10 flight cycles after November 12, 2014, or within 100 flight cycles after March 6, 2014 (the effective date of AD 2014-03-17), whichever occurs first, do a detailed visual inspection of each inboard flap fastener of the hinge-box forward fitting at WS 76.50 and WS 127.25, on both wings, to determine if the fasteners are correctly oriented and intact (non-fractured, with intact fastener head). Do the inspection in accordance with the Accomplishment Instructions of Bombardier Alert Service Bulletin A604-57-006, Revision 01, dated September 26, 2013, including Appendices 1 and 2, dated September 26, 2013, Revision 02, dated January 22, 2014, including Appendices 1 and 2, dated September 26, 2013, or Revision 04, dated November 12, 2014, including Appendices 1 and 2, dated September 26, 2013 (for serial numbers 5301 through 5665 inclusive); or Bombardier Alert Service Bulletin A605-57-004, Revision 01, dated September 26, 2013, including Appendices 1 and 2, dated September 26, 2013, Revision 02, dated January 22, 2014, including Appendices 1 and 2, dated September 26, 2013, or Revision 04, dated November 12, 2014, including Appendices 1 and 2, dated September 26, 2013 (for serial numbers 5701 through 5920 inclusive). As of the effective date of this AD, only use Bombardier Alert Service Bulletin A604-57-006, Revision 04, dated November 12, 2014, including Appendices 1 and 2, dated September 26, 2013; or Bombardier Alert Service Bulletin A605-57-004, Revision 04, dated November 12, 2014, including Appendices 1 and 2, dated September 26, 2013; as applicable; for the actions required by this paragraph.
(1) If all fasteners are found intact and correctly oriented, no further action is required by this AD.
(2) If any fastener is found fractured: Before further flight, remove and replace all forward and aft fasteners at WS 76.50 and WS 127.25, regardless of condition or orientation, on both wings, in accordance with the Accomplishment Instructions of the applicable service information identified in paragraph (g) of this AD. As of the effective date of this AD, only use Bombardier Alert Service Bulletin A604-57-006, Revision 04, dated November 12, 2014, including Appendices 1 and 2, dated September 26, 2013; or Bombardier Alert Service Bulletin A605-57-004, Revision 04, dated November 12, 2014, including Appendices 1 and 2, dated September 26, 2013; as applicable; for the actions required by this paragraph. After replacement of all fasteners as required by this paragraph of this AD, no further action is required by this AD.
(3) If any incorrectly oriented but intact fastener is found, and no fractured fastener is found, repeat the inspection required by paragraph (g) of this AD thereafter at intervals not to exceed 10 flight cycles, until the requirements of paragraph (i)(1) or (k) of this AD have been done.
This paragraph restates the requirements of paragraph (h) of AD 2014-17-51, with new service information. For airplanes on which an inspection required by paragraph (g) or (j) of AD 2014-03-17 has been done as of November 12, 2014 (the effective date of AD 2014-17-51), and on which any incorrectly oriented fastener, but no fractured fastener, was found: Except as provided by paragraph (i)(3) of this AD, do a detailed visual inspection of all inboard flap fasteners of the hinge-box forward fitting at WS 76.50 and WS 127.25, on both wings, to determine if the fasteners are intact (non-fractured, with intact fastener head). Inspect within 10 flight cycles after November 12, 2014, or within 100 flight cycles after the most recent inspection done as required by AD 2014-03-17, whichever occurs first. Inspect in accordance with the Accomplishment Instructions of the applicable service information identified in paragraph (g) of this AD. As of the effective date of this AD, only use Bombardier Alert Service Bulletin A604-57-006, Revision 04, dated November 12, 2014, including Appendices 1 and 2, dated September 26, 2013; or Bombardier Alert Service Bulletin A605-57-004, Revision 04, dated November 12, 2014, including Appendices 1 and 2, dated September 26, 2013; as applicable; for the actions required by this paragraph.
(1) If all fasteners are found intact, repeat the inspection thereafter at intervals not to exceed 10 flight cycles, until the requirements of paragraph (i)(1) or (k) of this AD have been done.
(2) If any fastener is found fractured: Before further flight, remove and replace all forward and aft fasteners at WS 76.50 and WS 127.25, regardless of condition or orientation, on both wings, in accordance with the Accomplishment Instructions of the applicable service information identified in paragraph (g) of this AD. As of the effective date of this AD, only use Bombardier Alert Service Bulletin A604-57-006, Revision 04, dated November 12, 2014, including Appendices 1 and 2, dated September 26, 2013; or Bombardier Alert Service Bulletin A605-57-004, Revision 04, dated November 12, 2014, including Appendices 1 and 2, dated September 26, 2013; as applicable; for the actions required by this paragraph. After replacement of all fasteners as required by this paragraph, no further action is required by this AD.
This paragraph restates the terminating action specified in paragraph (i) of AD 2014-17-51), with new service information.
(1) Replacement of all forward and aft fasteners at WS 76.50 and WS 127.25, on both wings, in accordance with the Accomplishment Instructions of the applicable service information identified in paragraph (g) of this AD, terminates the requirements of this AD. As of the effective date of this AD, only use Bombardier Alert Service Bulletin A604-57-006, Revision 04, dated November 12, 2014, including Appendices 1 and 2, dated September 26, 2013; or Bombardier Alert Service Bulletin A605-57-004, Revision 04, dated November 12, 2014, including Appendices 1 and 2, dated September 26, 2013; as applicable; for the actions specified in this paragraph.
(2) Accomplishment of the applicable requirements of this AD constitutes terminating action for the requirements of AD 2014-03-17 for that airplane only.
(3) Replacement of all fractured and incorrectly oriented fasteners before November 12, 2014 (the effective date of AD 2014-17-51), as provided by paragraph (i) or (k) of AD 2014-03-17, is acceptable for compliance with the requirements of this AD.
This paragraph restates the requirements of paragraph (j) of AD 2014-17-51. Special flight permits to operate the airplane to a location where the airplane can be repaired in accordance with 14 CFR 21.197 and 21.199 are not allowed.
For airplanes on which incorrectly oriented fasteners were found during any inspection required by paragraph (g), (g)(3), (h), or (h)(1) of this AD, but none were found to be fractured: Within 24 months after the effective date of this AD, remove and replace all forward and aft fasteners at WS 76.50 and WS 127.25, regardless of condition or orientation, on affected wings, in accordance with the Accomplishment Instructions of Bombardier Alert Service Bulletin A604-57-006, Revision 04, dated November 12, 2014, including Appendices 1 and 2, dated September 26, 2013 (for serial numbers 5301 through 5665 inclusive); or Bombardier Alert Service Bulletin A605-57-004, Revision 04, dated November 12, 2014, including Appendices 1 and 2, dated September 26, 2013 (for serial numbers 5701 through 5920 inclusive). Accomplishing the requirements of this paragraph terminates the requirements of this AD.
