Airworthiness Directive · Amendment 39-15422 · Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440) Airplanes
Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440) Airplanes
This AD applies to Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes, certificated in any category; as identified in Bombardier Service Bulletin 601R-53-061, Revision E, dated December 7, 2006.
We are adopting a new airworthiness directive (AD) for certain Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes. This AD requires repetitive detailed inspections for cracking of the left side and right side frame and reinforcement angles at fuselage station (FS) 640 between stringer 9 and stringer 12, and corrective actions if necessary. This AD also provides an optional terminating action for the repetitive inspections. This AD results from reports that cracks have been discovered on the frame and reinforcement angles at FS 640. We are issuing this AD to detect and correct cracking of the frame, which could lead to failure of the fuselage structure and possible loss 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.
Before the accumulation of 8,600 total flight cycles, or within 1,100 flight cycles after the effective date of this AD, whichever occurs later: Perform a detailed inspection to detect cracking of the left side and right side frames and reinforcement angles at FS640 between stringer 9 and stringer 12, in accordance with Part A of the Accomplishment Instructions of Bombardier Service Bulletin 601R-53-061, Revision E, dated December 7, 2006.
Note 1: For the purposes of this AD, a detailed inspection is: “An intensive examination of a specific item, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate. Inspection aids such as mirror, magnifying lenses, etc., may be necessary. Surface cleaning and elaborate procedures may be required.”
If no crack is found during the inspection required by paragraph (f) of this AD: Repeat the detailed inspection thereafter at intervals not to exceed 1,100 flight cycles, until the frame modification described in paragraph (h)(2) of this AD or the optional terminating modification described in paragraph (i) of this AD has been done.
(h) If any crack is found during the inspection required by paragraph (g) of this AD: Before further flight, repair the crack in accordance with paragraph (h)(1), (h)(2), or (h)(3) of this AD, as applicable.
(1) For any crack found in the frame at the stringer 9 cut-out only, repair in accordance with Part A of the Accomplishment Instructions of Bombardier Service Bulletin 601R-53-061, Revision E, dated December 7, 2006.
(2) For any crack found in the frame reinforcement doubler only, do the actions described in paragraphs (h)(2)(i) and (h)(2)(ii) of this AD.
(i) Do the frame modification (including related investigative and corrective actions) described in Part C of the Accomplishment Instructions of Bombardier Service Bulletin 601R-53-061, Revision E, dated December 7, 2006; except where the service bulletin specifies to contact the manufacturer for repair instructions, repair the crack using a method approved by either the Manager, New York Aircraft Certification Office (ACO), FAA; or Transport Canada Civil Aviation (TCCA) (or its delegated agent).
(ii) Within 12,000 flight cycles after doing the modification required by paragraph (h)(2)(i) of this AD, do the detailed inspection required by paragraph (f) of this AD, then repeat the detailed inspection thereafter at intervals not to exceed 1,100 flight cycles.
(3) For any crack found in areas of the inspection zone described in paragraph (f) of this AD other than those areas described in paragraphs (h)(1) and (h)(2) of this AD: Repair the crack using a method approved by either the Manager, New York ACO, FAA; or TCCA (or its delegated agent).
(i) Reinforcement of any engine support beam in accordance with the Accomplishment Instructions of the service information described in paragraph (i)(1) or (i)(2) of this AD, as applicable, ends all repetitive inspections required by this AD for that support beam.
(1) For all airplanes: If the reinforcement is done before the effective date of this AD, Bombardier Alert Service Bulletin A601R-53-059, Revision E, dated March 21, 2005; or Revision F, dated April 21, 2006; may be used. After the effective date of this AD, only Bombardier Alert Service Bulletin A601R-53-059, Revision F, may be used.
(2) For airplanes identified in Bombardier Service Bulletin 601R-53-065, Revision B, dated November 2, 2007: If the reinforcement is done before the effective date of this AD, Bombardier Service Bulletin 601R-53-065, Revision A, dated August 24, 2005, or Revision B, may be used. After the effective date of this AD, only Bombardier Service Bulletin 601R-53-065, Revision B, may be used.
Although Bombardier Service Bulletin 601R-53-061, Revision E, dated December 7, 2006, specifies to submit certain information to the manufacturer, this AD does not include that requirement.
The aircraft, engines and makers this AD names, by the model designations in its text. A model listed here may still be outside the AD's serial ranges.
