Bell Helicopter Textron Canada (BHTC) 22Bell Helicopter Textron Canada (BHTC) 222 Series Helicopters

Bell Helicopter Textron Canada (BHTC) 222 Series Helicopters

<table cellspacing="0" cellpadding="0" style="margin-top:0pt; margin-bottom:0pt; border-collapse:collapse"><tbody><tr><td style="width:74.35pt; padding-right:5.35pt; padding-left:5.35pt; vertical-align:top"><p><span>Applicability:</span></p></td><td style="width:414.55pt; padding-right:5.35pt; padding-left:5.35pt; vertical-align:top"><p><span>Bell Helicopter Textron Canada (BHTC) Models: 222, serial number 47006 through 47089; 222B, serial number 47131 through 47156; 222U, All.</span></p></td></tr><tr><td style="width:74.35pt; padding-right:5.35pt; padding-left:5.35pt; vertical-align:top"><p><span>Requirement:</span></p></td><td style="width:414.55pt; padding-right:5.35pt; padding-left:5.35pt; vertical-align:top"><p style="margin-left:21.3pt; text-indent:-21.3pt"><span>1.</span><span style="width:12.3pt; text-indent:0pt; display:inline-block"> </span><span>Verify the existing rigging of the tail rotor pitch change mechanism in accordance with the Accomplishment Instructions provided in the applicable Alert Service Bulletin (ASB) listed below, or later NAA approved revisions.</span></p><table cellspacing="0" cellpadding="0" style="margin-top:0pt; margin-bottom:0pt; border:0.75pt solid #000000; border-collapse:collapse"><tbody><tr><td style="width:196.1pt; border-right:0.75pt solid #000000; border-bottom:0.75pt solid #000000; padding-right:5.03pt; padding-left:5.03pt; vertical-align:top"><p style="text-align:center"><span>Helicopter Model</span></p></td><td style="width:196.1pt; border-left:0.75pt solid #000000; border-bottom:0.75pt solid #000000; padding-right:5.03pt; padding-left:5.03pt; vertical-align:top"><p style="text-align:center"><span>Applicable Alert Service Bulletin</span></p></td></tr><tr><td style="width:196.1pt; border-top:0.75pt solid #000000; border-right:0.75pt solid #000000; border-bottom:0.75pt solid #000000; padding-right:5.03pt; padding-left:5.03pt; vertical-align:top"><p style="text-align:center"><span>222 and 222B</span></p></td><td style="width:196.1pt; border-top:0.75pt solid #000000; border-left:0.75pt solid #000000; border-bottom:0.75pt solid #000000; padding-right:5.03pt; padding-left:5.03pt; vertical-align:top"><p style="text-align:center"><span>222-07-104 issued 9 January2007</span></p></td></tr><tr><td style="width:196.1pt; border-top:0.75pt solid #000000; border-right:0.75pt solid #000000; padding-right:5.03pt; padding-left:5.03pt; vertical-align:top"><p style="text-align:center"><span>222U</span></p></td><td style="width:196.1pt; border-top:0.75pt solid #000000; border-left:0.75pt solid #000000; padding-right:5.03pt; padding-left:5.03pt; vertical-align:top"><p style="text-align:center"><span>222U-07-75 issued 9 January2007</span></p></td></tr></tbody></table><p style="margin-left:21.3pt; margin-bottom:12pt; text-indent:-21.3pt"><span>2.</span><span style="width:12.3pt; text-indent:0pt; display:inline-block"> </span><span>Verify if the tail rotor yoke replacement is required, as per Item 3 of Accomplishment Instructions of applicable ASB.</span><span> </span><span>If required; replace the yoke with airworthy part.</span></p><p style="margin-top:12pt; margin-left:21.3pt; margin-bottom:12pt; text-indent:-21.3pt"><span>3.</span><span style="width:12.3pt; text-indent:0pt; display:inline-block"> </span><span>Perform a new rigging procedure as per Accomplishment Instructions of the applicable ASB or later NAA approved revisions.</span></p><p class="Note" style="margin-top:12pt"><span>Note:</span><span> </span><span>Transport </span><span>Canada</span><span> AD CF 2007-07 dated 11 April 2007 refers.</span></p></td></tr><tr><td style="width:74.35pt; padding-right:5.35pt; padding-left:5.35pt; vertical-align:top"><p><span>Compliance:</span></p></td><td style="width:414.55pt; padding-right:5.35pt; padding-left:5.35pt; vertical-align:top"><p><span>At the next 150 hour or annual inspection but no later than 31 December 2007, unless already accomplished.</span></p></td></tr><tr><td style="width:74.35pt; padding-right:5.35pt; padding-left:5.35pt; vertical-align:top"><p><span></span></p></td><td style="width:414.55pt; padding-right:5.35pt; padding-left:5.35pt; vertical-align:top"><p><span>This Airworthiness Directive becomes effective on 2 August 2007.</span></p></td></tr><tr><td style="width:74.35pt; padding-right:5.35pt; padding-left:5.35pt; vertical-align:top"><p><span>Background:</span></p></td><td style="width:414.55pt; padding-right:5.35pt; padding-left:5.35pt; vertical-align:top"><p><span>It has been determined that the existing rigging procedures for the tail rotor pitch change mechanism have to be changed due to possibility of parts interference.</span><span> </span><span>This AD mandates verification of the tail rotor pitch change mechanism and new rigging procedures.</span></p></td></tr></tbody></table>