Airworthiness Directive · Amendment 39-17676 · Flight controls
Bombardier, Inc. Airplanes
This AD applies to Bombardier, Inc. Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes, certificated in any category, serial numbers 7003 and subsequent.
We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes. This AD was prompted by reports of fractured rudder pedal tubes installed on the pilot-side rudder bar assembly. This AD requires repetitive inspections for cracking and damage of both pilot-side rudder pedal tubes, and replacement of affected pilot-side rudder bar assemblies if necessary. We are issuing this AD to detect and correct cracking of both pilot-side rudder pedal tubes, which could result in loss of pilot rudder pedal input causing reduced yaw controllability or a runway excursion.
You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.
At the applicable time specified in paragraphs (g)(1) through (g)(6) of this AD, do a detailed or eddy current inspection for cracking and damage (i.e., corrosion or cracking) of both pilot-side rudder pedal tubes having part number (P/N) 600-90204-3, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 601R-27-162, including Appendix A, dated April 5, 2013.
(1) For airplanes that have accumulated less than 20,000 total flight cycles as of the effective date of this AD: Do the inspection before the accumulation of 23,000 total flight cycles.
(2) For airplanes that have accumulated 20,000 total flight cycles or more, but less than 25,000 total flight cycles as of the effective date of this AD: Do the inspection within 3,000 flight cycles after the effective date of this AD, but not to exceed 26,300 total flight cycles.
(3) For airplanes that have accumulated 25,000 total flight cycles or more, but less than 30,000 total flight cycles as of the effective date of this AD: Do the inspection within 1,300 flight cycles after the effective date of this AD, but not to exceed 30,800 total flight cycles.
(4) For airplanes that have accumulated 30,000 total flight cycles or more, but less than 33,000 total flight cycles as of the effective date of this AD: Do the inspection within 800 flight cycles after the effective date of this AD, but not to exceed 33,500 total flight cycles.
(5) For airplanes that have accumulated 33,000 total flight cycles or more, but less than 37,000 total flight cycles as of the effective date of this AD: Do the inspection within 500 flight cycles after the effective of this AD, but not to exceed 37,300 total flight cycles.
(6) For airplanes that have accumulated 37,000 total flight cycles or more as of the effective date of this AD: Do the inspection within 300 flight cycles after the effective date of this AD.
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 a mirror, magnifying lenses, etc., may be necessary. Surface cleaning and elaborate procedures may be required.
For any tube on which no cracking and no damage is found during any inspection required by paragraph (g) of this AD: At the applicable time specified in paragraph (i)(1) or (i)(2) of this AD, repeat the detailed or eddy current inspection for cracking of the pilot-side rudder pedal tubes, specified in paragraph (g) of this AD, until the terminating action specified in paragraph (k) of this AD has been accomplished.
(1) If the most recent inspection was a detailed inspection: Repeat the inspection within 600 flight cycles thereafter.
(2) If the most recent inspection was an eddy current inspection: Repeat the inspection within 1,000 flight cycles thereafter.
(1) If any cracking is found around the aft tapered holes during any inspection required by paragraph (g) or (i) of this AD, before further flight, replace the affected rudder bar assemblies, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 601R-27-162, including Appendix A, dated April 5, 2013.
(2) If any other damage (i.e., corrosion or cracking), other than that specified in paragraph (j)(1) of this AD, is found during any inspection required by paragraph (g) or (i) of this AD, before further flight, repair using a method approved by either the Manager, New York Aircraft Certification Office (ACO), ANE-170, FAA; or Transport Canada Civil Aviation (TCCA) (or its delegated agent).
Replacement of both pilot-side rudder bar assemblies, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 601R-27-162, including Appendix A, dated April 5, 2013, terminates the inspections required by paragraphs (g) and (i) of this AD.
