Airworthiness Directive · Amendment 39-14106 · Bombardier Model CL-600-1A11 (CL-600), CL-600-2A12 (CL-601), and CL-600-2B16 (CL-601-3A, CL-601-3R, and CL-604) Airplanes Modified by Supplemental Type Certificate (STC) SA4900SW
Bombardier Model CL-600-1A11 (CL-600), CL-600-2A12 (CL-601), and CL-600-2B16 (CL-601-3A, CL-601-3R, and CL-604) Airplanes Modified by Supplemental Type Certificate (STC) SA4900SW
This AD applies to Bombardier Model CL-600-1A11 (CL-600), CL-600-2A12 (CL-601), and CL-600-2B16 (CL-601-3A, CL-601-3R, and CL-604) airplanes; certificated in any category; modified by STC SA4900SW; excluding serial number (S/N) 3025; and including but not limited to the serial numbers listed in Table 1 of this AD.
| Model | Known S/Ns |
|---|---|
| CL-600-1A11 (CL-600) | 1054, 1059, 1069, 1071, 1080 |
| CL-600-2A12 (CL-601) | 3012, 3013, 3034, 3045, 3050, 3051, 3061, 3065 |
| CL-600-2B16 (CL-601-3A, CL-601-3R, and CL-604) | 5012, 5046, 5060 |
The FAA is adopting a new airworthiness directive (AD) for certain Bombardier Model CL-600-1A11 (CL-600), CL-600-2A12 (CL-601), and CL-600-2B16 (CL-601-3A, CL-601-3R, and CL-604) airplanes modified by STC SA4900SW. This AD requires revising the airplane flight manual (AFM) to require repetitive visual checks of the microphone jack assemblies on both control columns to detect damage that may interfere with movement of the control column. This AD also requires modification of the microphone jack assembly, related investigative actions, and corrective actions if necessary, which allows the AFM revision to be removed from the AFM. This AD is prompted by a report of a rejected take-off and subsequent runway overrun due to restricted movement of the co-pilot's control column, which resulted in collapse of the nose landing gear and consequent damage of the forward fuselage. We are issuing this AD to prevent a damaged microphone jack assembly from interfering with movement of the control column, which could result in loss of control of the airplane.
You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.
Within 5 days after the effective date of this AD, revise the Limitations and Normal Procedures section of the AFM to contain the following information. This may be done by inserting a copy of this AD in the AFM.
“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. This check must be performed by the flightcrew. Any damage that may interfere with the movement of the control column must be repaired before further flight.”
Note 1: 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.
At the applicable compliance time specified in paragraph (g)(1) or (g)(2) of this AD, modify the microphone jack assembly and do 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 paragraph (h) of this AD. Once this modification is complete, the AFM revision required by paragraph (f) of this AD may be removed from the AFM. Although the service bulletin specifies reporting accomplishment of the service bulletin to the manufacturer, this AD does not require that action.
(1) 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 required by paragraph (f) of this AD: Before further flight.
(2) If no damage that may interfere with the movement of the control column is found during any visual check performed in accordance with the AFM revision required by paragraph (f) of this AD: Within 15 days or 15 flight hours after the effective date of this AD, whichever is first.
If any cracking is found during any inspection required by this AD, 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, and the service bulletin specifies contacting Raytheon for appropriate action: Before further flight, repair the cracking or do other applicable corrective actions according to a method approved by the Manager, Special Certification Office, ASW-190, FAA. For a repair or corrective action method to be approved by the Manager, Special Certification Office, as required by this paragraph, the Manager's approval letter must specifically refer to this AD.
Note 2: A note in the Accomplishment Instructions of the Raytheon service bulletin instructs operators to contact Raytheon if any difficulty is encountered in accomplishing the service bulletin. However, any deviation from the instructions provided in the service bulletin must be approved as an alternative method of compliance (AMOC) under paragraph (i) of this AD.
The aircraft, engines and makers this AD names, by the model designations in its text. A model listed here may still be outside the AD's serial ranges.
