Summary
We propose to supersede an existing airworthiness directive (AD) that applies to certain Bombardier Inc. Model CL-215-1A10 and CL- 215-6B11 (CL-215T Variant) airplanes. The existing AD currently requires repetitive inspections to detect cracking of the lower cap of the wing front and rear spars at wing station (WS) 51.00, and the wing lower skin. Additional actions, if cracking is found, include reworking the lower cap of the front or rear spar, inspecting for cracking, and repairing any cracking. The existing AD also requires reporting inspection results. Since we issued that AD, we have received reports of cracking found outside the inspection area. This proposed AD would extend the inspection area of the rear spar lower cap from WS 51.00 to WS 49.50 and modify the ultrasonic inspection calibration procedure. We are proposing this AD to detect and correct cracking of the lower caps of the wing front spar and rear spar, and lower wing skin, which could result in reduced structural integrity of the airplane.