Airworthiness Directive · Amendment 39-11972 · Bombardier Model CL-600-2B16 (CL-604) Series Airplanes
Bombardier Model CL-600-2B16 (CL-604) Series Airplanes
Model CL-600-2B16 (CL-604) series airplanes, serial numbers 5301 through 5374 inclusive, certificated in any category.
Note 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (e) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it.
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Bombardier Model CL-600-2B16 (CL-604) series airplanes. This action requires, among other actions, a general visual inspection to detect gaps between the vane bracket(s) and the adjacent skin; corrective actions, if necessary; and replacement of the six flap vane actuator beams with new beams. This action is necessary to detect and correct corrosion of the inboard flap actuator beam assembly and gaps between the vane brackets and adjacent skin, which could compromise the structural integrity of the flap systems and reduce the controllability of the airplane in the event that a flap vane actuator or a flap vane bracket fails during flight. This action is intended to address the identified unsafe condition.
To detect and correct corrosion of the inboard flap actuator beam assembly and gaps between the vane brackets and adjacent skin, which could compromise the structural integrity of the flap systems and reduce the controllability of the airplane in the event that a flap vane actuator or a flap vane bracket fails during flight, accomplish the following:
(a) Do a general visual inspection to detect gaps between the vane bracket(s), part number (P/N) 600-14306-1 and -2, and the adjacent skin, per paragraph “2. Accomplishment Instructions,” of Bombardier Alert Service Bulletin A604-27-006, dated April 18, 2000; at the time specified in paragraph (a)(1), (a)(2), or (a)(3) of this AD, as applicable.
(1) For airplanes having serial numbers 5301 through 5334 inclusive: Within 30 days after the effective date of this AD.
(2) For airplanes having serial numbers 5335 through 5354 inclusive: Within 90 days after the effective date of this AD.
(3) For airplanes having serial numbers 5355 through 5374 inclusive: Within 180 days after the effective date of this AD.
Note 2: For the purposes of this AD, a general visual inspection is defined as “A visual examination of an interior or exterior area, installation, or assembly to detect obvious damage, failure, or irregularity. This level of inspection is made under normally available lighting conditions such as daylight, hangar lighting, flashlight, or drop-light, and may require removal or opening of access panels or doors. Stands, ladders, or platforms may be required to gain proximity to the area being checked.”
(b) If any gap is found during the general visual inspection required by paragraph (a) of this AD, before further flight, perform a non-destructive inspection to detect cracks of the vane bracket, per paragraph “2. Accomplishment Instructions,” of Bombardier Alert Service Bulletin A604-27-006, dated April 18, 2000.
(1) If any crack is detected, before further flight, replace the cracked vane bracket with a new vane bracket per the service bulletin.
(2) If no crack is detected and if the gap is up to 0.100 inch (2.54 mm), eliminate the gap by filling the gap with liquid shim or installing a solid shim, as applicable, per the service bulletin.
(3) If no crack is detected and if the gap is more than 0.100 inch (2.54 mm), before further flight, repair in accordance with a method approved by the Manager, New York Aircraft Certification Office (ACO), FAA; or the Transport Canada Civil Aviation, (or its delegated agent). For a repair method to be approved by the Manager, New York ACO, as required by this paragraph, the Manager's approval letter must specifically reference this AD.
(c) Replace the six flap vane actuator beams with new beams, per paragraph “2. Accomplishment Instructions,” of Bombardier Alert Service Bulletin A604-27-006, dated April 18, 2000; at the time specified in paragraph (a)(1), (a)(2), or (a)(3) of this AD, as applicable.
(1) For airplanes having serial numbers 5301 through 5334 inclusive: Within 30 days after the effective date of this AD.
(2) For airplanes having serial numbers 5335 through 5354 inclusive: Within 90 days after the effective date of this AD.
(3) For airplanes having serial numbers 5355 through 5374 inclusive: Within 180 days after the effective date of this AD.
(d) Within 30 days after doing the replacement required by paragraph (c) of this AD, forward any cracked vane bracket and any two of the six removed flap vane actuator assemblies to Bombardier, per paragraph “2. Accomplishment Instructions,” of Bombardier Alert Service Bulletin A604-27-006, dated April 18, 2000. Data, such as the station location of the flap actuator beam assembly, the number of flight hours and landings of the airplane at removal, must be submitted along with the flap vane actuator beam assemblies. Information collection requirements contained in this regulation have been approved by the Office of Management and Budget (OMB) under the provisions of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et seq.) and have been assigned OMB Control Number 2120-0056.
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.
