Airworthiness Directive · Amendment 39-17999 · Wings
Bombardier, Inc. Airplanes
Superseded. A later AD replaced this one: AD 2016-08-15. Comply with the one in force.
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 adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model CL-600-2B16 airplanes. This emergency AD was sent previously to all known U.S. owners and operators of these airplanes. This AD requires 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. This AD also provides for optional terminating action for the requirements of the AD. This AD was prompted by reports of fractured fastener heads on the inboard flap hinge-box forward fitting at WS 76.50 due to incorrect installation. We are issuing this AD to detect and correct incorrectly oriented or fractured fasteners, which 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.
For airplanes on which the actions required by AD 2014-03-17, Amendment 39-17754 (79 FR 9389, February 19, 2014), have not been done as of the effective date of this AD: Within 10 flight cycles after the effective date of this AD, or within 100 flight cycles after March 6, 2014 (the effective date of AD 2014-03-17, Amendment 39-17754 (79 FR 9389, February 19, 2014)), 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, or Revision 02, dated January 22, 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, or Revision 02, dated January 22, 2014, including Appendices 1 and 2, dated September 26, 2013 (for serial numbers 5701 through 5920 inclusive).
(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 Bombardier Alert Service Bulletin A604-57-006, Revision 01, dated September 26, 2013, including Appendices 1 and 2, dated September 26, 2013, or Revision 02, dated January 22, 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, or Revision 02, dated January 22, 2014, including Appendices 1 and 2, dated September 26, 2013 (for serial numbers 5701 through 5920 inclusive). After replacement of all fasteners as required by paragraph (g)(2) 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) of this AD have been done.
For airplanes on which an inspection required by paragraph (g) or (j) of AD 2014-03-17, Amendment 39-17754 (79 FR 9389, February 19, 2014), has been done as of the effective date of this AD, 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 the effective date of this AD, 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 Bombardier Alert Service Bulletin A604-57-006, Revision 01, dated September 26, 2013, including Appendices 1 and 2, dated September 26, 2013, or Revision 02, dated January 22, 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, or Revision 02, dated January 22, 2014, including Appendices 1 and 2, dated September 26, 2013 (for serial numbers 5701 through 5920 inclusive).
(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) 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 Bombardier Alert Service Bulletin A604-57-006, Revision 01, dated September 26, 2013, including Appendices 1 and 2, dated September 26, 2013, or Revision 02, dated January 22, 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, or Revision 02, dated January 22, 2014, including Appendices 1 and 2, dated September 26, 2013 (for serial numbers 5701 through 5920 inclusive). After replacement of all fasteners as required by paragraph (h)(2) of this AD, no further action is required by this AD.
(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 Bombardier Alert Service Bulletin A604-57-006, Revision 01, dated September 26, 2013, including Appendices 1 and 2, dated September 26, 2013, or Revision 02, dated January 22, 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, or Revision 02, dated January 22, 2014, including Appendices 1 and 2, dated September 26, 2013 (for serial numbers 5701 through 5920 inclusive); terminates the requirements of this AD.
(2) Accomplishment of the applicable requirements of this AD constitutes terminating action for the requirements of AD 2014-03-17, Amendment 39-17754 (79 FR 9389, February 19, 2014), for that airplane only.
(3) Replacement, before the effective date of this AD, of all fractured and incorrectly oriented fasteners, as provided by paragraph (i) or (k) of AD 2014-03-17, Amendment 39-17754 (79 FR 9389, February 19, 2014), is acceptable for compliance with the requirements of this AD.
