Airworthiness directives › 2014-13-15
AD 2014-13-15 Airworthiness Directives; EADS CASA (Type Certificate Previously Held by Construcciones Aeronauticas, S.A.) Airplanes
Models named: CN-235-300. Read the applicability below — it usually turns on serial or part numbers too.
Applicability*9
This AD applies to EADS CASA (Type Certificate previously held by Construcciones Aeronauticas, S.A.) Model CN-235-300 airplanes, certificated in any category, manufacturer serial numbers (MSN) C-143 through C-208, inclusive.
Compliance
Comply with this AD within the compliance times specified, unless already done.
Required actions
For airplanes having MSNs C-143 through C-195 inclusive, C-201, and C-202: At the applicable time specified in paragraph (g)(1) or (g)(2) of this AD, do a detailed inspection to determine the presence of panel thickness reduction of the lower panel joint with the side panels at stringer (STR) 24 left-hand and STR24 right-hand, in accordance with Airbus Military All Operator Letter (AOL) 235-024, Revision 01, dated March 1, 2013. (1) For airplane versions CG01, CL04, ED01, GC01, MM01, and SM01: Inspect at the later of the times specified in paragraphs (g)(1)(i) and (g)(1)(ii) of this AD. (i) Before the accumulation of 1,900 total flight cycles. (ii) Within 10 flight cycles or 30 days after the effective date of this AD, whichever occurs first. (2) For any airplane version not identified in paragraph (g)(1) of this AD: Inspect at the later of the times specified in paragraphs (g)(2)(i) and (g)(2)(ii) of this AD. (i) Before the accumulation of 3,800 total flight cycles. (ii) Within 10 flight cycles or 30 days after the effective date of this AD, whichever occurs first.
Unsafe condition
This AD was prompted by reports of reduced thickness of the center fuselage lower skin panel. We are issuing this AD to detect and correct a reduced thickness of lower panel joints, which could result in reduced fatigue and damage tolerant characteristics of the lower panel joint to the adjacent side panels and lead to failure of the center fuselage lower skin panel, resulting in loss of control of the airplane.
Affected ADs
None.
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The directive text above is reproduced from the Federal Register, a work of the United States government and in the public domain. The separation into applicability, compliance and required actions is TrackAD's.*1