Airworthiness directives › 2012-11-04
AD 2012-11-04 Airworthiness Directives; Bombardier Inc. Airplanes
Applicability*9
This AD applies to the Bombardier Inc. airplanes; certificated in any category; as identified in paragraphs (c)(1) and (c)(2) of this AD. (1) Model CL-215-1A10 (Water Bomber) airplanes, serial numbers 1001 through 1125 inclusive. (2) Model CL-215-6B11 (CL-215T Variant) airplanes, serial numbers 1056 through 1125 inclusive.
Compliance
You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.
Required actions
This paragraph restates the requirements of paragraph (f) of AD 2005-18-05, Amendment 39-14245 (70 FR 52009, September 1, 2005), with new service information. At the time specified in paragraph (h) of this AD: Perform an ultrasonic inspection to detect cracking of the lower cap of the wing front and rear spars at wing station 51, in accordance with the Accomplishment Instructions of Canadair Alert Service Bulletin 215-A463, Revision 1, dated May 25, 1995, or Bombardier Alert Service Bulletin 215-A463, Revision 2, dated March 13, 2001 (for the front spar); and Canadair Alert Service Bulletin 215-A454, Revision 1, dated May 25, 1995, Bombardier Alert Service Bulletin 215-A454, Revision 2, dated January 27, 1999, Bombardier Alert Service Bulletin 215-A454, Revision 3, dated March 13, 2001, or Bombardier Alert Service Bulletin 215-A454, Revision 4, dated November 18, 2009 (for the rear spar). As of the effective date of this AD, the inspection must be done in accordance with the Accomplishment Instructions of Bombardier Alert Service Bulletin 215-A463, Revision 2, dated March 13, 2001 (for the front spar); and Bombardier Alert Service Bulletin 215-A454, Revision 3, dated March 13, 2001, or Bombardier Alert Service Bulletin 215-A454, Revision 4, dated November 18, 2009 (for the rear spar).
Unsafe condition
This AD was prompted by reports of cracking found outside the inspection area. We are issuing this AD to detect and correct cracking of the lower caps of the wing front and rear spars, and lower wing skin, which could result in reduced structural integrity of the airplane.
Affected ADs
This AD supersedes AD 2005-18-05, Amendment 39-14245 (70 FR 52009, September 1, 2005).
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The directive text above is reproduced from the Federal Register, a work of the United States government and in the public domain. The separation into applicability, compliance and required actions is TrackAD's.*1