Airworthiness Directive · Amendment 39-17067 · Wings
Bombardier Inc. Airplanes
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.
We are superseding an existing airworthiness directive (AD) for certain Bombardier Inc. Model CL-215-1A10 and CL-215-6B11 (CL-215T Variant) airplanes. That 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. This new AD requires extending the inspection area of the rear spar lower cap from WS 51.00 to WS 49.50 and modifying the ultrasonic inspection calibration procedure. 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.
You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.
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).
This paragraph restates the requirements of paragraph (g) of AD 2005-18-05, Amendment 39-14245 (70 FR 52009, September 1, 2005). Do the inspections required by paragraph (g) of this AD at the earlier of the times specified in paragraphs (h)(1) and (h)(2) of this AD.
(1) Prior to the accumulation of 3,000 total flight hours, or within 25 flight hours after March 4, 1998 (the effective date of AD 98-04-08, Amendment 39-10321 (63 FR 7640, February 17, 1998)), whichever occurs later.
(2) At the later of the times specified in paragraphs (h)(2)(i) and (h)(2)(ii) of this AD.
(i) Prior to the accumulation of 2,500 total flight hours, or 8,000 total water drops, whichever occurs first.
(ii) Within 50 flight hours or 150 water drops after October 6, 2005 (the effective date of AD 2005-18-05, Amendment 39-14245 (70 FR 52009, September 1, 2005), whichever occurs first.
This paragraph restates the requirements of paragraph (h) of AD 2005-18-05, Amendment 39-14245 (70 FR 52009, September 1, 2005), with new intervals. Repeat the ultrasonic inspection specified in paragraph (g) of this AD at the times specified in paragraph (i)(1) or (i)(2) of this AD, as applicable.
(1) For airplanes on which any ultrasonic inspection required by paragraph (a) of AD 98-04-08, Amendment 39-10321 (63 FR 7640, February 17, 1998), has been done before October 6, 2005: Within 600 flight hours after the last ultrasonic inspection, do the ultrasonic inspection specified in paragraph (g) of this AD. Repeat the ultrasonic inspection specified in paragraph (g) of this AD thereafter at intervals not to exceed 600 flight hours or 2,000 water drops, whichever occurs first.
(2) For airplanes on which the ultrasonic inspection required by paragraph (a) of AD 98-04-08, Amendment 39-10321 (63 FR 7640, February 17, 1998), has not been done before October 6, 2005: After accomplishing the initial ultrasonic inspection specified in paragraph (g) of this AD, repeat the ultrasonic inspection specified in paragraph (g) of this AD thereafter at intervals not to exceed 600 flight hours or 2,000 water drops, whichever occurs first.
This paragraph restates the requirements of paragraph (i) of AD 2005-18-05, Amendment 39-14245 (70 FR 52009, September 1, 2005), with new service information. At the later of the times specified in paragraphs (j)(1) and (j)(2) of this AD, do an ultrasonic inspection for cracks of the wing lower skin, in accordance with the Accomplishment Instructions of 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. Thereafter, do the ultrasonic inspection for cracks of the wing lower skin at the times specified for the ultrasonic inspection in paragraph (i) of this AD.
(1) Within 50 flight hours or 150 water drops after October 6, 2005, whichever occurs first.
(2) Before further flight after accomplishing the first ultrasonic inspection required by paragraph (g) or (i) of this AD after October 6, 2005.
This paragraph restates the requirements of paragraph (j) of AD 2005-18-05, Amendment 39-14245 (70 FR 52009, September 1, 2005), with new service information. If any cracking is detected during any inspection required by paragraph (g), (i), or (j) of this AD, before further flight, accomplish paragraphs (k)(1) and (k)(2) of this AD.
(1) Rework the lower cap of the front or rear spar, as applicable, 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).
(2) After doing the rework specified in paragraph (k)(1) of this AD, do a general visual inspection, from inside the wing box, to detect cracks of the front spar web or rear spar web, as applicable, and the lower skin area, 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 (for the rear spar); or Bombardier Alert Service Bulletin 215-A454, Revision 4, dated November 18, 2009 (for the rear spar). If any cracking is detected: Before further flight, repair in accordance with a method approved by the Manager, New York Aircraft Certification Office (ACO), FAA; or Transport Canada Civil Aviation (TCCA) (or its delegated agent).
This paragraph provides credit for the actions required by paragraphs (g) and (h) of this AD, if those actions were performed before October 6, 2005, using Canadair Alert Service Bulletin 215-A463, dated April 8, 1993; Canadair Alert Service Bulletin 215-A463, Revision 1, dated May 25, 1995; Canadair Alert Service Bulletin 215-A454, dated October 13, 1993; Canadair Alert Service Bulletin 215-A454, Revision 1, dated May 25, 1995; or Bombardier Alert Service Bulletin 215-A454, Revision 2, dated January 27, 1999.
(2) This paragraph provides credit for the actions required by paragraphs (g) and (h) of this AD, if those actions were performed before October 6, 2005, using Bombardier Alert Wire 215-A454, dated December 23, 1992; and Bombardier Alert Wire 215-A463, dated March 26, 1993.
This paragraph restates the requirements of paragraph (m) of AD 2005-18-05, Amendment 39-14245 (70 FR 52009, September 1, 2005), with new contact information. For any inspection required by AD 2005-18-05, that is accomplished after October 6, 2005, within 30 days after accomplishing the inspection, submit a report of any inspection results (both positive and negative findings) to Bombardier, Inc., Canadair, Aerospace Group, P.O. Box 6087, Station Centre-ville, Montreal, Quebec H3C 3G9, Canada; or to Bombardier, Inc., 400 Côte-Vertu Road West, Dorval, Québec H4S 1Y9, Canada; telephone 514-855-5000; fax 514-855-7401; email thd.crj@aero.bombardier.com; Internet http://www.bombardier.com. As of the effective date of this AD, submit reports to Bombardier, Inc., in accordance with the contact information specified in Bombardier Alert Service Bulletin 215-A454, Revision 4, dated November 18, 2009.
Within the compliance time specified in paragraph (p) of this AD: Perform an ultrasonic inspection to detect cracking of the right and left wing rear spar lower cap between wing station (WS) 51.00 and WS 49.50, in accordance with paragraph 2.C., “Part A,” of the Accomplishment Instructions of Bombardier Alert Service Bulletin 215-A454, Revision 4, dated November 18, 2009. Repeat the ultrasonic inspection thereafter at intervals not to exceed 600 flight hours or 2,000 water drops, whichever comes first. Accomplishment of the actions in this paragraph terminates the inspection requirements of the lower cap of the wing rear spars at WS 51.00 of paragraph (g) of this AD. Accomplishment of the actions in this paragraph does not terminate the inspection requirements of the lower cap of the wing front spars at WS 51.00 required by paragraph (g) of this AD.
(1) If any crack is found in the rear spar lower cap, before further flight, do a general visual inspection for cracks from inside the wing box, of the areas of the rear spar web and the wing lower skin adjacent to the crack in the rear spar lower cap, in accordance with paragraph 2.C., “Part A,” of the Accomplishment Instructions of Bombardier Alert Service Bulletin 215-A454, Revision 4, dated November 18, 2009.
(2) If any cracking is detected during any ultrasonic or general visual inspection required by paragraph (n) of this AD, before further flight, repair in accordance with a method approved by the Manager, New York ACO, FAA; or TCCA (or its delegated agent).
Within the compliance time specified in paragraph (p) of this AD: Perform an ultrasonic inspection to detect cracking of the wing lower skin underneath the drag angle between the front spar and the rear spar at the left and right WS 51.00, in accordance with paragraph 2.D., “Part B,” of the Accomplishment Instructions of Bombardier Alert Service Bulletin 215-A454, Revision 4, dated November 18, 2009. Do the ultrasonic inspection thereafter at intervals not to exceed 600 flight hours or 2,000 water drops, whichever comes first. Accomplishment of the actions in this paragraph terminates the requirements of paragraph (j) of this AD.
(1) If any crack is found in the wing lower skin, before further flight, do a general visual inspection for cracks from inside the wing box, i.e., the stringers adjacent to the skin crack, in accordance with paragraph 2.D., “Part B,” of the Accomplishment Instructions of Bombardier Alert Service Bulletin 215-A454, Revision 4, dated November 18, 2009.
(2) If any cracking is detected during any ultrasonic or general visual inspection required by paragraph (n) of this AD, before further flight, repair in accordance with a method approved by the Manager, New York ACO, FAA; or TCCA (or its delegated agent).
At the later of the times specified in paragraphs (p)(1) and (p)(2) of this AD.
(1) Prior to the accumulation of 2,500 total flight hours, or 8,000 total water drops, whichever occurs first.
(2) Within 50 flight hours or 150 water drops after the effective date of this AD, whichever occurs first.
