Airworthiness Directive · Amendment 39-17913 · Flight controls
Bombardier, Inc. Airplanes
This AD applies to the airplanes identified in paragraphs (c)(1), (c)(2), and (c)(3) of this AD, certificated in any category.
(1) Bombardier, Inc. Model CL-600-2C10 (Regional Jet Series 700, 701, & 702) airplanes, serial numbers 10002 through 10342 inclusive.
(2) Bombardier, Inc. Model CL-600-2D15 (Regional Jet Series 705), and Model CL-600-2D24 (Regional Jet Series 900) airplanes, serial numbers 15001 through 15337 inclusive.
(3) Bombardier, Inc. Model CL-600-2E25 (Regional Jet Series 1000) airplanes, serial numbers 19001 through 19040 inclusive.
We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model CL-600-2C10 (Regional Jet Series 700, 701, & 702) airplanes, Model CL-600-2D15 (Regional Jet Series 705) airplanes, Model CL-600-2D24 (Regional Jet Series 900) airplanes, and Model CL- 600-2E25 (Regional Jet Series 1000) airplanes. This AD was prompted by two in-service reports of fracture of the rudder pedal tubes installed on the pilot-side rudder bar assembly. This AD requires repetitive inspections for cracking and damage of the pilot-side rudder pedal tubes, and corrective action if necessary. This AD also provides optional terminating action for the repetitive inspections. We are issuing this AD to detect and correct cracked and damaged pilot-side rudder pedal tubes, which could result in loss of function of the pilot's rudder pedal during flight, takeoff, or landing, and could result in reduced controllability of the airplane.
Before the accumulation of 26,000 total flight cycles or within 3 months after the effective date of this AD, whichever occurs later: Perform a detailed or eddy current inspection for cracking around the aft tapered holes of both pilot-side rudder pedal tubes, and for damage of the rudder pedal tubes in locations other than around the aft tapered holes, in accordance with Part A of the Accomplishment Instructions of Bombardier Service Bulletin 670BA-27-065, including Appendix A, dated November 15, 2013. Repeat the inspection thereafter at the applicable intervals specified in paragraph (g)(1) or (g)(2) of this AD, until the terminating action specified in paragraph (i) of this AD is done.
(1) If the most recent inspection was a detailed inspection: Within 750 flight cycles after doing the detailed inspection.
(2) If the most recent inspection was an eddy current inspection: Within 1,250 flight cycles after doing the eddy current inspection.
(1) If any crack is found around the aft tapered holes during any inspection required by paragraph (g) of this AD, before further flight, replace the rudder bar assembly, in accordance with Part B of the Accomplishment Instructions of Bombardier Service Bulletin 670BA-27-065, including Appendix A, dated November 15, 2013.
(2) If any damage is found during any inspection required by paragraph (g) of this AD in a location other than around the aft tapered holes: Before further flight, repair using a method approved by the Manager, New York ACO, ANE-170, Engine and Propeller Directorate, FAA; or Transport Canada Civil Aviation (TCCA); or Bombardier, Inc.'s TCCA Design Approval Organization (DAO). If approved by the DAO, the approval must include the DAO-authorized signature.
Replacement of both pilot-side rudder bar assemblies, in accordance with Part B of the Accomplishment Instructions of Bombardier Service Bulletin 670BA-27-065, including Appendix A, dated November 15, 2013, constitutes terminating action for the repetitive inspections required by paragraph (g) of this AD.
