Division Bombardier (Canadair) CL-600 (Challenger - AD/CL-600/65 - Control Column Microphone Jack Modification - FAA STC SA4900SW - Bombardier (Canadair) CL-600 (Challenger) Series Aeroplanes

Bombardier (Canadair) CL-600 (Challenger) Series Aeroplanes

AD/CL-600/65	Control Column Microphone JackModification - FAA STC SA4900SW	8/2005 TX

<table cellspacing="0" cellpadding="0" style="width:510.3pt; 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 colspan="2" style="width:414.55pt; padding-right:5.35pt; padding-left:5.35pt; vertical-align:top"><p><span>Model CL-600-1A11 (CL-600), CL-600-2A12 (CL-601) and CL-600-2B16</span><br><span>(CL-601-3A, CL-601-3R, and CL- 604) aeroplanes; modified by </span><span>United States</span><span> federal Aviation Administration (FAA) Supplemental Type Certificate (STC) SA4900SW, excluding serial number 3025 and including, but not limited to, the following serial numbers:</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:201.9pt; padding-right:5.35pt; padding-left:5.35pt; vertical-align:top"><p><span style="width:36pt; display:inline-block"></span><span style="font-weight:bold">Model</span><br><span>CL-600-1A11 (CL-600)</span><br><span>CL-600-2A12 (CL-601)</span><br><br><span>CL-600-2B16 (CL-601-3A, CL-601-3R and CL-604)</span></p></td><td style="width:201.95pt; padding-right:5.35pt; padding-left:5.35pt; vertical-align:top"><p><span style="width:36pt; display:inline-block"></span><span style="font-weight:bold">Serial Numbers</span><br><span>1054, 1059, 1069, 1071, 1080</span><br><span>3012, 3013, 3034, 3045, 3050, 3051, 3061, 3065</span><br><span>5012, 5046, 5060</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 colspan="2" 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>Revise the Limitations and Normal Procedures section of the Aircraft Flight manual (AFM) to contain the following information:</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 colspan="2" style="width:414.55pt; padding-right:5.35pt; padding-left:5.35pt; vertical-align:top"><p style="margin-left:42.55pt; text-indent:-0.55pt"><span>"Before every flight, perform a visual check of the microphone jack assembly on the pilot's and co-pilot's control column to detect damage that may interfere with movement of the control column, including downward bending of the receptacle.</span><span> </span><span>This check must be performed by the flight crew.</span><span> </span><span>Any damage that may interfere with the movement of the control column must be repaired before further flight."</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 colspan="2" style="width:414.55pt; padding-right:5.35pt; padding-left:5.35pt; vertical-align:top"><p style="margin-left:21.3pt"><span>Revision of the AFM may be accomplished by inserting a copy of this Directive in the AFM.</span></p></td></tr><tr><td style="width:74.35pt; padding-right:5.35pt; padding-left:5.35pt; vertical-align:top"><p class="Note"><span></span></p></td><td colspan="2" style="width:414.55pt; padding-right:5.35pt; padding-left:5.35pt; vertical-align:top"><p class="Note"><span>Note 1:</span><span> </span><span>Bombardier Advisory Wire AW600-00-2247, Revision 2, dated March 24, 2005, provides additional information on damaged microphone jack assemblies and interference of damaged assemblies with movement of the control column.</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 colspan="2" 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>2.</span><span style="width:12.3pt; text-indent:0pt; display:inline-block"> </span><span>Modify the microphone jack assembly and perform all related investigative actions and applicable corrective actions, in accordance with the Accomplishment Instructions of Raytheon Service Bulletin SB 23-3727, dated May 2005, except as provided by Requirement 3.</span><span> </span><span>Once this modification is complete, the AFM revision required by Requirement 1 may be removed from the AFM.</span></p></td></tr></tbody></table>

	3. If any cracking is found during any inspection required by this Directive or if the distance between existing and new fastener holes is less than the limit specified in Raytheon Service Bulletin SB 23-3727, dated May 2005, repair the cracking or carry out any other applicable corrective action.
	Note 2: Contact Raytheon Aircraft Company Arkansas Technical Support in accordance with SB 23-3727 for advice regarding repair or corrective action.
	Note 3: FAA AD 2005-11-04 Amdt 39-14106 refers.
Compliance:	For Requirement 1 - Within five days after the effective date of this Directive.
	For Requirement 2:
	a. If damage that may interfere with the movement of the control column is found during any visual check performed in accordance with the AFM revision - Before further flight.
	b. If damage that may interfere with the movement of the control column is not found during any visual check performed in accordance with the AFM revision - Within 15 days or 15 hours time in service after the effective date of this Directive, whichever occurs first.
	For Requirement 3 - Before further flight immediately following discovery of the anomaly.
	This Airworthiness Directive becomes effective on 16 June 2005.
Background:	This Directive is issued to prevent a damaged microphone jack assembly from interfering with movement of the control column, which could result in loss of control of the aeroplane.The FAA has received a report indicating that a Model CL-600-1A11 (CL-600) aeroplane experienced a rejected take-off and subsequently overran the runway. The nose landing gear collapsed, and the forward fuselage was damaged as a result of the incident. The flight crew reported that, when they attempted to take off, the control column would not move aft beyond the neutral position. Investigation revealed that the microphone jack assembly installed on the co-pilot's control column was bent downward, which restricted the aft movement of the control column.

Bombardier (Canadair) CL-600 (ChallengerBombardier (Canadair) CL-600 (Challenger) Series Aeroplanes

Get a plain-English read of Bombardier (Canadair) CL-600 (Challenger

Bombardier (Canadair) CL-600 (Challenger) Series Aeroplanes