Airworthiness directives › 2014-11-10
AD 2014-11-10 Airworthiness Directives; Bombardier, Inc. Airplanes
Applicability*9
This AD applies to Bombardier, Inc. Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes, certificated in any category, serial numbers (S/Ns) 7003 through 8110 inclusive.
Compliance
Comply with this AD within the compliance times specified, unless already done.
Required actions
This paragraph restates the requirements of paragraph (g) of AD 2008-08-09, Amendment 39-15461 (73 FR 19979, April 14, 2008), with revised service information. For airplanes having S/Ns 7003 through 7990 inclusive, and S/Ns 8000 through 8110 inclusive: Before the accumulation of 4,000 total flight hours, or within 100 flight hours after March 27, 2006 (the effective date of AD 2006-05-11 R1, Amendment 39-14528 (71 FR 15323, March 28, 2006), whichever occurs later, do a functional test of the pilot input lever of the PFS units to determine if the lever is disconnected, in accordance with the Accomplishment Instructions of a service bulletin specified in paragraph (g)(1), (g)(2), or (g)(3) of this AD. Repeat the test at intervals not to exceed 100 flight hours. As of the effective date of this AD, only Bombardier Alert Service Bulletin A601R-27-144, Revision E, dated October 2, 2012, including Appendix A, Revision A, dated December 20, 2006, may be used to accomplish the actions required by this paragraph. (1) Bombardier Alert Service Bulletin A601R-27-144, Revision A, dated February 14, 2006, including Appendix A, dated September 15, 2005. (2) Bombardier Alert Service Bulletin A601R-27-144, Revision B, dated December 20, 2006, including Appendix A, Revision A, dated December 20, 2006. (3) Bombardier Alert Service Bulletin A601R-27-144, Revision E, dated October 2, 2012, including Appendix A, Revision A, dated December 20, 2006.
Unsafe condition
This AD was prompted by reports that the shear pin in the input lever of several pitch feel simulator (PFS) units failed due to fatigue; and by the development of a re-designed PFS unit, which eliminates the need for repetitive functional testing. We are issuing this AD to prevent undetected failure of the shear pins of both PFS units simultaneously, which could result in loss of pitch feel forces and consequent reduced control of the airplane.
Affected ADs
This AD supersedes AD 2008-08-09, Amendment 39-15461 (73 FR 19979, April 14, 2008).
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