Airworthiness directives › 2018-20-20
AD 2018-20-20 Airworthiness Directives; Bombardier, Inc., Airplanes
Models named: BD-700-1A10, BD-700-1A11. Read the applicability below — it usually turns on serial or part numbers too.
Applicability*9
This AD applies to Bombardier, Inc., Model BD-700-1A10 and BD-700-1A11 airplanes, certificated in any category, serial numbers 9492 through 9711 inclusive, 9713 through 9717 inclusive, 9719 through 9726 inclusive, 9728, 9730, 9732, 9733, 9743, and 9751.
Compliance
Comply with this AD within the compliance times specified, unless already done.
Required actions
Within 60 months after the effective date of this AD, or before accumulating 7,500 total flight cycles, whichever occurs first: Do an eddy current inspection of the support brackets of the elevator bell crank, part number (P/N) GD248-8750-3 and P/N GD248-8750-4, for any cracking at the fastener holes, and do a measurement to confirm that the fastener hole diameters are within tolerance, as applicable, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 700-27-5009, Revision 02, dated June 15, 2018 (for Model BD-700-1A11 airplanes); or Bombardier Service Bulletin 700-27-6009, Revision 01, dated July 18, 2017 (for Model BD-700-1A10 airplanes). If any cracking is found or if any fastener hole is out of tolerance, before further flight, replace with a new support bracket, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 700-27-5009, Revision 02, dated June 15, 2018 (for Model BD-700-1A11 airplanes); or Bombardier Service Bulletin 700-27-6009, Revision 01, dated July 18, 2017 (for Model BD-700-1A10 airplanes).
Unsafe condition
This AD was prompted by a report of cracking at the fastener holes of the left-hand-side support bracket of the elevator bell crank for the control linkage in the vertical stabilizer. We are issuing this AD to address any cracking in the support bracket of the elevator bell crank, which could lead to detachment of the bracket and loss of functionality of the elevator on the affected side, and result in reduced controllability of the airplane. Failure of both brackets could result in loss of pitch control of the airplane.
Affected ADs
None.
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The directive text above is reproduced from the Federal Register, a work of the United States government and in the public domain. The separation into applicability, compliance and required actions is TrackAD's.*1