EASA AD CF-2002-39R2
Fuselage Pressure Floor Skin
Summary
Airworthiness Directive CF-2002-39R2 addresses the fuselage pressure floor skin on Bombardier Inc. model CL-600-2B19 aeroplanes, serial numbers 7003 through 8999. This directive mandates revised inspection requirements to detect and correct fatigue cracks that could lead to rapid decompression during flight. It updates maintenance schedules and inspection tasks to enhance structural safety of the affected aircraft.
What Changed
CF-2002-39R2 corrects the Temporary Revision number referenced for the introduction of Airworthiness Limitation Task 53-41-193. It supersedes the previous revision CF-2002-39R1 and clarifies inspection requirements and phase-in schedules for different serial number groups. The directive also updates inspection tasks and intervals based on recent maintenance manual revisions.
Why It Matters
This directive is critical for operators and maintenance organizations to prevent structural failure of the fuselage pressure floor skin, which is a principal structural element. Compliance ensures early detection of fatigue cracks, reducing the risk of rapid decompression and enhancing flight safety. It also provides clear guidance on inspection intervals and approved repair procedures, aiding compliance teams in meeting regulatory requirements.
What To Do
Operators of Bombardier CL-600-2B19 aircraft with serial numbers 7003 through 8999 must revise their approved maintenance schedules within 30 days of the previous revision's effective date by incorporating updated inspection tasks 53-41-149 or 53-41-193 as applicable. Initial inspections must be completed according to specified flight cycle thresholds, with repeat inspections every 10,000 flight cycles if no cracks are found. Any detected damage must be repaired before further flight using approved instructions referencing this directive.
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