Airworthiness directives › 2013-22-04
AD 2013-22-04 Airworthiness Directives; Bombardier, Inc. Airplanes
Models named: DHC-8-102, -103, -106, -201, -202, -301, -311, -315, DHC-8-400, -401. Read the applicability below — it usually turns on serial or part numbers too.
Applicability*9
This AD applies to Bombardier, Inc. airplanes, certificated in any category, as specified in paragraphs (c)(1) and (c)(2) of this AD. (1) Model DHC-8-102, -103, -106, -201, -202, -301, -311, and -315 airplanes: Serial numbers 003 through 672 inclusive. (2) Model DHC-8-400, -401, and -402 airplanes: Serial numbers 4003 through 4372 inclusive.
Compliance
You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.
Required actions
For Model DHC-8-102, -103, -106, -201, -202, -301, -311, and -315 airplanes: Within 6,000 flight hours or 24 months after the effective date of this AD, whichever occurs first, inspect each bellcrank for cracking using liquid penetrant, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 8-27-111, dated June 15, 2011. (1) If no cracking is found: Before further flight, rework the bellcrank, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 8-27-111, dated June 15, 2011. (2) If any clevis hole is greater than 0.218 inch (measured edge-to-edge), or if any cracking is found: Before further flight, replace the bellcrank with a new bellcrank, or with a serviceable bellcrank with bushings having part number 82710297-101 installed, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 8-27-111, dated June 15, 2011.
Unsafe condition
This AD was prompted by reports of excessive wear found in the clevis (bolt) hole where the rod assembly attaches to the rudder/brake pedal bellcrank, due to prolonged fretting. We are issuing this AD to detect and correct a worn or cracked clevis hole, which could cause failure of the bellcrank on one side, with subsequent asymmetric braking and consequent runway excursion.
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