Airworthiness Directive · Amendment 39-18939 · Engine exhaust
Bombardier, Inc., Airplanes
This AD applies to Bombardier, Inc., Model CL-600-1A11 (CL-600) airplanes, certificated in any category, serial numbers 1004 through 1085 inclusive.
We are superseding Airworthiness Directive (AD) 2014-16-02, which applied to certain Bombardier, Inc., Model CL-600-1A11 (CL-600) airplanes. AD 2014-16-02 required revising the airplane flight manual to prohibit thrust reverser operation, doing repetitive detailed inspections of both engine thrust reversers for cracks, and modifying the thrust reversers if necessary. The modification is also an interim (optional) terminating action for the repetitive inspections. This new AD adds a new terminating modification of the thrust reversers, which includes new inspections and repair, if necessary. This AD was prompted by a determination that it is necessary to add a requirement to repair or modify the thrust reversers, which would terminate the requirements of AD 2014-16-02. We are issuing this AD to address the unsafe condition on these products.
This paragraph restates the requirements of paragraph (g) of AD 2014-16-02, with revised service information. Within 1 calendar day after August 12, 2014 (the effective date of AD 2014-16-02): Revise the applicable sections of the AFM to include the information specified in the temporary revisions (TRs) identified in paragraphs (g)(1) and (g)(2) of this AD, as applicable. These TRs introduce procedures to prohibit thrust reverser operation. Operate the airplane according to the limitations and procedures in the TRs identified in paragraphs (g)(1) and (g)(2) of this AD, as applicable. The revision required by paragraph (g) of this AD may be done by inserting copies of the applicable TRs identified in paragraphs (g)(1) and (g)(2) of this AD into the AFM. When these TRs have been included in the general revisions of the AFM, the general revisions may be inserted in the AFM, provided the relevant information in the general revision is identical to that in the applicable TRs, and the TRs may be removed.
(1) Canadair TR 600/29, dated June 20, 2014, to the Canadair CL-600-1A11 AFM; or Canadair TR 600/29-2, dated January 18, 2016, to the Canadair CL-600-1A11 AFM. As of the effective date of this AD, use only Canadair TR 600/29-2, dated January 18, 2016, to the Canadair CL-600-1A11 AFM.
(2) Canadair TR 600-1/24, dated June 20, 2014, to the Canadair CL-600-1A11 AFM (Winglets), including Erratum, Publication No. PSP 600-1AFM (US), TR No. 600-1/24, June 20, 2014; or Canadair TR 600-1/24-2, dated January 18, 2016, to the Canadair CL-600-1A11 AFM (Winglets). As of the effective date of this AD, use only Canadair TR 600-1/24-2, dated January 18, 2016, to the Canadair CL-600-1A11 AFM (Winglets).
This paragraph restates the requirements of paragraph (h) of AD 2014-16-02, with revised service information. Within 25 flight cycles or 90 days, whichever occurs first, after August 12, 2014 (the effective date of AD 2014-16-02), do detailed inspections (including a borescope inspection) of both engine thrust reversers for cracks, in accordance with the Accomplishment Instructions of Bombardier Alert Service Bulletin A600-0769, Revision 01, dated June 26, 2014; or Bombardier Alert Service Bulletin A600-0769, Revision 02, dated February 22, 2016. As of the effective date of this AD, use only Bombardier Alert Service Bulletin A600-0769, Revision 02, dated February 22, 2016.
(1) If no cracking is found during any inspection required by paragraph (h) of this AD, repeat the inspection required by paragraph (h) of this AD thereafter at intervals not to exceed 100 flight cycles until the repair or modification specified in paragraph (i) or (k) of this AD is done.
(2) If any cracking is found during any inspection required by paragraph (h) of this AD, before further flight, modify the thrust reversers on both engines, in accordance with Part B of the Accomplishment Instructions of Bombardier Alert Service Bulletin A600-0769, Revision 01, dated June 26, 2014; or Bombardier Alert Service Bulletin A600-0769, Revision 02, dated February 22, 2016. As of the effective date of this AD, use only Bombardier Alert Service Bulletin A600-0769, Revision 02, dated February 22, 2016.
This paragraph restates the optional terminating action specified in paragraph (i) of AD 2014-16-02, with revised service information. Modifying the thrust reversers on both engines, in accordance with Part B of the Accomplishment Instructions of Bombardier Alert Service Bulletin A600-0769, Revision 01, dated June 26, 2014; or Bombardier Alert Service Bulletin A600-0769, Revision 02, dated February 22, 2016; terminates the inspections required by paragraph (h) of this AD. As of the effective date of this AD, use only Bombardier Alert Service Bulletin A600-0769, Revision 02, dated February 22, 2016.
This paragraph restates the credit provided in paragraph (j) of AD 2014-16-02, with no changes. This paragraph provides credit for actions required by paragraphs (h) and (i) of this AD, if those actions were performed before August 12, 2014 (the effective date of AD 2014-16-02), using Bombardier Alert Service Bulletin A600-0769, dated June 19, 2014.
Within 24 months after the accomplishing the modification specified in paragraph (h)(2) of this AD, or within 48 months after accomplishing the initial inspection required by paragraph (h) of this AD, whichever occurs later: Modify the thrust reversers on both engines, including doing the inspections specified in paragraphs (k)(1) through (k)(6) of this AD, in accordance with Part C of the Accomplishment Instructions of Bombardier Alert Service Bulletin A600-0769, Revision 02, dated February 22, 2016, except as required by paragraphs (m)(1) and (m)(2) of this AD. Modification of all thrust reversers terminates the requirements of paragraphs (g), (h), and (i) of this AD.
(1) Do general visual inspections of the flipper doors for cracks.
(2) Do a general visual inspection of the thrust reverser skin, frames, joints, splices, and fasteners for cracks.
(3) Do a general visual inspection of the thrust reverser for cracks.
(4) Do liquid penetrant or eddy current inspections, as applicable, of the frames for cracks.
(5) Do a detailed visual inspection of the frames for cracks and elongated holes, and do a liquid penetrant inspection of the frames for cracks.
(6) Do a liquid penetrant or an eddy current inspection of the translating sleeve skin for cracks.
If, during any inspection required by paragraph (k) of this AD, any cracking or elongated hole is found, before further flight, repair using a method approved by the Manager, New York Aircraft Certification Office (ACO), ANE-170, FAA; or Transport Canada Civil Aviation (TCCA); or Bombardier, Inc.'s TCCA Design Approval Organization (DAO).
(1) If it is not possible to follow all instructions specified in Bombardier Alert Service Bulletin A600-0769, Revision 02, dated February 22, 2016, during accomplishment of the actions required by paragraph (k) of this AD, before further flight, repair using a method approved by the Manager, New York ACO, ANE-170, FAA; or TCCA; or Bombardier, Inc.'s TCCA DAO.
(2) Where Bombardier Alert Service Bulletin A600-0769, Revision 02, dated February 22, 2016, specifies to contact Bombardier if shim thickness is over the applicable thicknesses identified in Bombardier Alert Service Bulletin A600-0769, Revision 02, dated February 22, 2016, before further flight, repair using a method approved by the Manager, New York ACO, ANE-170, FAA; or TCCA; or Bombardier, Inc.'s TCCA DAO.
