Airworthiness Directive · Amendment 39-17463 · Wings
Bombardier, Inc. Airplanes
Superseded. A later AD replaced this one: AD 2019-02-05. Comply with the one in force.
This AD applies to Bombardier, Inc. Model CL-215-1A10 airplanes, serial numbers (S/Ns) 1001 through 1125 inclusive; and Model CL-215-6B11 (CL-215T Variant) airplanes, S/Ns 1056 through 1125 inclusive; certificated in any category.
We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model CL-215-1A10 and CL-215-6B11 (CL-215T Variant) airplanes. This AD requires repetitive detailed inspections for cracking of the left-hand (LH) and right-hand (RH) wing lower skin, and repair if necessary. This AD also provides terminating action for the repetitive detailed inspections. This AD was prompted by reports of a fractured wing lower rear spar cap and reinforcing strap. We are issuing this AD to detect and correct cracked wing structure, which could result in failure of the wing.
You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.
Within 10 flight hours after the effective date of this AD, do a detailed inspection for cracking of the left-hand (LH) and right-hand (RH) wing lower skin between wing stations (WS) 45.00 and 51.00, in accordance with Part A of Bombardier Alert Service Bulletin 215-A558, dated April 5, 2013. Repeat the inspection thereafter at intervals not to exceed 25 flight hours, until the inspection specified in paragraph (h)(1) or (h)(2) of this AD has been accomplished. If any cracking is found during the inspection required by paragraph (g) of this AD, before further flight, repair the crack using a method approved by the Manager, New York Aircraft Certification Office (ACO), FAA; or Transport Canada Civil Aviation (TCCA) (or its delegated agent).
(1) Accomplishing a one-time detailed inspection for cracking of the LH and RH wing lower skin, front and rear spar caps, front and rear spar webs, and reinforcing straps, in accordance with Part B of Bombardier Alert Service Bulletin 215-A558, dated April 5, 2013, terminates the actions required by paragraph (g) of this AD. If any cracking is found during the one-time detailed inspection, before further flight, repair the crack using a method approved by the Manager, New York ACO, FAA; or TCCA (or its delegated agent).
(2) Accomplishing a one-time eddy current inspection for cracking of the LH and RH wing lower front and rear spar caps, in accordance with paragraph 3.B. and paragraphs 4. through 9. (Part C-1), and paragraphs 10. through 16. (Part C-2), of Bombardier Alert Service Bulletin 215-A558, dated April 5, 2013, terminates the actions required by paragraph (g) of this AD. If any cracking is found during the one-time eddy current inspection, before further flight, repair the crack using a method approved by the Manager, New York ACO, FAA; or TCCA (or its delegated agent).
Submit a report of the crack findings of the inspections specified in paragraphs (g), (h)(1), and (h)(2) of this AD to Bombardier Aerospace Specialized and Amphibious Aircraft Technical Support at email: mtl.saa.tech.support@aero.bombardier.com. Submit the report at the applicable time specified in paragraph (i)(1) or (i)(2) of this AD. The report must include the inspection results, a description of any discrepancies found, the airplane serial number, and the number of landings and flight hours on the airplane.
(1) If the inspection was done on or after the effective date of this AD: Submit the report within 14 days after the inspection.
(2) If the inspection was done before the effective date of this AD: Submit the report within 14 days after the effective date of this AD.
