EASA AD CF-2014-07R1
Fuselage — Cracking of Skin Panels and Skin Splice Joints and Angles at Stringers 6 and 20 between Fuselage Station 409.00 and 589.00
Summary
Airworthiness Directive CF-2014-07R1 addresses cracking issues in the fuselage skin panels and skin splice joints and angles at stringers 6 and 20 between fuselage stations 409.00 and 589.00 on MHI RJ Aviation ULC model CL-600-2B19 aircraft, serial numbers 7003 through 7990, 8000 and subsequent. This directive mandates revisions to maintenance schedules and inspection tasks to detect multiple site damage that could compromise structural integrity and lead to rapid decompression. It also requires structural modifications to prevent widespread fatigue damage in affected aircraft.
What Changed
This revision supersedes AD CF-2014-07 and corrects previous omissions in inspection requirements along stringer 20, specifically under the forward and aft fairings. It mandates the incorporation of a revised Airworthiness Limitation task 53-41-207, replacing earlier tasks 53-41-109, 53-41-205, and 53-41-206. Additionally, it clarifies compliance timelines and provides equivalency for certain Repair Engineering Orders.
Why It Matters
The directive is critical for operators and maintenance organizations to prevent undetected multiple site damage that could reduce fuselage structural strength and risk rapid decompression. Compliance ensures continued airworthiness and safety of the CL-600-2B19 fleet by addressing fatigue cracking not covered under previous maintenance programs. It also guides maintenance planning and structural repairs to maintain regulatory compliance and aircraft integrity.
What To Do
Operators must amend their Transport Canada approved maintenance schedules within 60 days of the original AD effective date (14 February 2014) and again within 60 days of this revision's effective date (27 July 2020) to incorporate the specified AWL tasks. Initial inspections must be completed within 2000 flight cycles for aircraft with over 38,000 total flight cycles as of 14 February 2014. Any detected cracking requires contacting MHI RJ Aviation ULC for approved repairs before further flight. Structural modifications must be incorporated before reaching 60,000 total flight cycles.
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