Airworthiness Directive · Amendment 39-18687 · Wings
Bombardier, Inc. Airplanes
This AD applies to the Bombardier, Inc. airplanes identified in paragraphs (c)(1), (c)(2), and (c)(3) of this AD, certificated in any category.
(1) Bombardier, Inc. Model CL-600-1A11 (CL-600) airplanes, having serial numbers (S/Ns) 1004 through 1085 inclusive.
(2) Bombardier, Inc. Model CL-600-2A12 (CL-601) airplanes, having S/Ns 3001 through 3066 inclusive.
(3) Bombardier, Inc. Model CL-600-2B16 (CL-601-3A and CL-601-3R Variants) airplanes, having S/Ns 5001 through 5194 inclusive.
We are superseding Airworthiness Directive (AD) 2015-02-23, for certain Bombardier, Inc. Model CL-600-1A11 (CL-600), CL-600-2A12 (CL-601), and CL-600-2B16 (CL-601-3A and CL-601-3R Variants) airplanes. AD 2015-02-23 required repetitive inspections for fractured or incorrectly oriented fasteners on the inboard flap hinge-box forward fittings on both wings, and replacement of all fasteners if necessary. This new AD also requires replacement of the fasteners, which terminates the requirements of this AD. This AD was prompted by reports of incorrectly oriented fasteners. We are issuing this AD to prevent incorrectly oriented or fractured fasteners, which could result in detachment of the flap hinge-box and the flap surface, and consequent reduced controllability of the airplane.
This paragraph restates the requirements of paragraph (g) of AD 2015-02-23, with no changes. For airplanes that have not been inspected as required by paragraph (g) of AD 2014-03-17, as of February 18, 2015 (the effective date of AD 2015-02-23): Within 10 flight cycles after February 18, 2015, or 100 flight cycles after March 6, 2014 (the effective date of AD 2014-03-17), whichever occurs first, do a detailed visual inspection for incorrect orientation and any fractured or missing fastener heads of each inboard flap fastener of the hinge-box forward fitting at wing station (WS) 76.50 and WS 127.25, on both wings, in accordance with the Accomplishment Instructions of the applicable service information specified in paragraphs (g)(1) and (g)(2) of this AD. Accomplishing the inspection required by this paragraph terminates the requirements of paragraph (g) of AD 2014-03-17 for the inspected airplane only.
(1) For Model CL-600-1A11 (CL-600) airplanes having S/Ns 1004 through 1085 inclusive: Bombardier Alert Service Bulletin A600-0763, Revision 02, dated December 9, 2014, including Appendixes 1 and 2, dated September 26, 2013.
(2) For Model CL-600-2A12 (CL-601) airplanes having S/Ns 3001 through 3066 inclusive, and Model CL-600-2B16 (CL-601-3A and CL-601-3R Variants) airplanes having S/Ns 5001 through 5194 inclusive: Bombardier Alert Service Bulletin A601-0627, Revision 02, dated December 9, 2014, including Appendixes 1 and 2, dated September 26, 2013.
(1) This paragraph restates the requirements of paragraph (h)(1) of AD 2015-02-23, with no changes. If, during any inspection required by paragraph (g) of this AD, all fasteners are found correctly oriented and not fractured, and no fastener heads are missing (fasteners found intact): No further action is required by this AD.
(2) This paragraph restates the requirements of paragraph (h)(2) of AD 2015-02-23, with revised references to replacement paragraphs. If, during any inspection required by paragraph (g) of this AD, any fastener is found incorrectly oriented but no fasteners are fractured or are missing a fastener head (fasteners found intact), repeat the inspection required by paragraph (g) of this AD thereafter at intervals not to exceed 10 flight cycles until the replacements specified in paragraphs (h)(3), (k), or (n) of this AD are accomplished.
(3) This paragraph restates the requirements of paragraph (h)(3) of AD 2015-02-23, with no changes. If, during any inspection required by paragraph (g) of this AD, any fastener is found fractured or has a missing fastener head: Before further flight, remove and replace all forward and aft fasteners (regardless of orientation or condition) at WS 76.50 and WS 127.25, on both wings, in accordance with the Accomplishment Instructions of the applicable service information specified in paragraphs (h)(3)(i) and (h)(3)(ii) of this AD, except as required by paragraph (m) of this AD. After accomplishing the replacements required by this paragraph, no further action is required by this AD.
(i) For Model CL-600-1A11 (CL-600) airplanes having S/Ns 1004 through 1085 inclusive: Bombardier Alert Service Bulletin A600-0763, Revision 02, dated December 9, 2014, including Appendixes 1 and 2, dated September 26, 2013.
(ii) For Model CL-600-2A12 (CL-601) airplanes having S/Ns 3001 through 3066 inclusive, and Model CL-600-2B16 (CL-601-3A and CL-601-3R Variants) airplanes having S/Ns 5001 through 5194 inclusive: Bombardier Alert Service Bulletin A601-0627, Revision 02, dated December 9, 2014, including Appendixes 1 and 2, dated September 26, 2013.
This paragraph restates the requirements of paragraph (i) of AD 2015-02-23, with no changes. For airplanes on which an inspection required by paragraph (g) or (j) of AD 2014-03-17, has been done as of the effective date of this AD, and on which any incorrectly oriented fastener was found but no fasteners were fractured (fasteners found intact): Except as provided by paragraph (l) of this AD, within 10 flight cycles after February 18, 2015 (the effective date of AD 2015-02-23), or within 100 flight cycles after accomplishing the most recent inspection required by AD 2014-03-17, whichever occurs first, do a detailed visual inspection for any fractured or missing fastener heads of each inboard flap fastener of the hinge-box forward fitting at WS 76.50 and WS 127.25, on both wings. Do the inspection in accordance with the Accomplishment Instructions of the applicable service information specified in paragraphs (i)(1) and (i)(2) of this AD. Accomplishing the inspection required by this paragraph terminates the requirements of paragraphs (g) and (j) of AD 2014-03-17 for the inspected airplane only.
(1) For Model CL-600-1A11 (CL-600) airplanes having S/Ns 1004 through 1085 inclusive: Bombardier Alert Service Bulletin A600-0763, Revision 02, dated December 9, 2014, including Appendixes 1 and 2, dated September 26, 2013.
(2) For Model CL-600-2A12 (CL-601) airplanes having S/Ns 3001 through 3066 inclusive, and Model CL-600-2B16 (CL-601-3A and CL-601-3R Variants) airplanes having S/Ns 5001 through 5194 inclusive: Bombardier Alert Service Bulletin A601-0627, Revision 02, dated December 9, 2014, including Appendixes 1 and 2, dated September 26, 2013.
(1) This paragraph restates the requirements of paragraph (j)(1) of AD 2015-02-23, with revised reference to additional, new requirements. If, during any inspection required by paragraph (i) of this AD, no fasteners are found fractured or have missing fastener heads (fasteners are intact), repeat the inspection required by paragraph (i) of this AD thereafter at intervals not to exceed 10 flight cycles until the replacement specified in paragraph (j)(2), (k), or (n) of this AD is accomplished.
(2) This paragraph restates the requirements of paragraph (j)(2) of AD 2015-02-23, with no changes. If, during any inspection required by paragraph (i) of this AD, any fastener is found fractured or has a missing fastener head: Before further flight, remove and replace all forward and aft fasteners (regardless of orientation or condition) at WS 76.50 and WS 127.25, on both wings, in accordance with the Accomplishment Instructions of the applicable service information specified in paragraphs (j)(2)(i) and (j)(2)(ii) of this AD, except as required by paragraph (m) of this AD. After accomplishing the replacements required by this paragraph, no further action is required by this AD.
(i) For Model CL-600-1A11 (CL-600) airplanes having S/Ns 1004 through 1085 inclusive: Bombardier Alert Service Bulletin A600-0763, Revision 02, dated December 9, 2014, including Appendixes 1 and 2, dated September 26, 2013.
(ii) For Model CL-600-2A12 (CL-601) airplanes having S/Ns 3001 through 3066 inclusive, and Model CL-600-2B16 (CL-601-3A and CL-601-3R Variants) airplanes having S/Ns 5001 through 5194 inclusive: Bombardier Alert Service Bulletin A601-0627, Revision 02, dated December 9, 2014, including Appendixes 1 and 2, dated September 26, 2013.
This paragraph restates the provisions of paragraph (k) of AD 2015-02-23, with no changes. Replacement of all forward and aft fasteners (regardless of orientation or condition) at WS 76.50 and WS 127.25, on both wings, terminates the requirements of this AD. The replacement must be done in accordance with the Accomplishment Instructions of the applicable service information specified in paragraphs (k)(1) and (k)(2) of this AD, except as provided by paragraph (m) of this AD. Doing the replacements specified in this paragraph terminates the requirements of paragraphs (g) and (j) of AD 2014-03-17, only for the airplane on which the replacement was done.
(1) For Model CL-600-1A11 (CL-600) airplanes having S/Ns 1004 through 1085 inclusive: Bombardier Alert Service Bulletin A600-0763, Revision 02, dated December 9, 2014, including Appendixes 1 and 2, dated September 26, 2013.
(2) For Model CL-600-2A12 (CL-601) airplanes having S/Ns 3001 through 3066 inclusive, and Model CL-600-2B16 (CL-601-3A and CL-601-3R Variants) airplanes having S/Ns 5001 through 5194 inclusive: Bombardier Alert Service Bulletin A601-0627, Revision 02, dated December 9, 2014, including Appendixes 1 and 2, dated September 26, 2013.
This paragraph restates the provisions of paragraph (l) of AD 2015-02-23, with no changes. Replacement of all fractured and incorrectly oriented forward and aft fasteners, as specified in paragraph (i) or (k) of AD 2014-03-17, if done before the effective date of this AD, is considered acceptable for compliance with the requirements of this AD.
This paragraph restates the requirements of paragraph (m) of AD 2015-02-23, with no changes. Where Bombardier Alert Service Bulletin A600-0763, Revision 02, dated December 9, 2014, including Appendixes 1 and 2, dated September 26, 2013; and Bombardier Alert Service Bulletin A601-0627, Revision 02, dated December 9, 2014, including Appendixes 1 and 2, dated September 26, 2013; specify to contact Bombardier for repair instructions, before further flight, repair using a method approved by the Manager, New York Aircraft Certification Office (ACO), FAA; or Transport Canada Civil Aviation (TCCA); or Bombardier's TCCA Design Approval Organization (DAO).
For airplanes on which any incorrectly oriented fastener, and no fractured or missing fastener, was detected during any inspection required by paragraph (g), (h)(2), (i), and (j)(1) of this AD: Within 24 months after the effective date of this AD, replace all forward and aft fasteners, regardless of condition or orientation, at WS 76.50 and WS 127.25, on affected wings, in accordance with the Accomplishment Instructions of the applicable service information specified in paragraphs (k)(1) and (k)(2) of this AD, except as provided by paragraph (m) of this AD. Doing the replacements specified in this paragraph terminates the requirements of this AD. Doing the replacements specified in this paragraph terminates the requirements of paragraphs (g) and (j) of AD 2014-03-17, only for the airplane on which the replacement was done.
