Airworthiness directives › 2017-01-04
AD 2017-01-04 Airworthiness Directives; Fokker Services B.V. Airplanes
Models named: F28 Mark 0100. Read the applicability below — it usually turns on serial or part numbers too.
Applicability*9
This AD applies to Fokker Services B.V. Model F28 Mark 0100 airplanes, certificated in any category, serial numbers 11244 through 11407 inclusive.
Compliance
Comply with this AD within the compliance times specified, unless already done.
Required actions
Within the compliance time specified in paragraphs (g)(1) and (g)(2) of this AD, as applicable, do high and low frequency eddy current inspections for cracks in the fuselage skin around the largest traffic collision avoidance system (TCAS) antenna external doubler and of the longitudinal lap joint at fuselage stringer STR37 between fuselage station (STA) STA6805 and STA7305, in accordance with the Accomplishment Instructions of Fokker Service Bulletin SBF100-53-130, dated December 1, 2015. (1) For airplanes having 45,000 or more total flight cycles as of the effective date of this AD, since the date of issuance of the original airworthiness certificate or the date of issuance of the original export certificate of airworthiness: Do the high and low frequency eddy current inspections within 750 flight cycles after the effective date of this AD. (2) For airplanes having 40,000 or more total flight cycles, but less than 45,000 total flight cycles as of the effective date of this AD, since the date of issuance of the original airworthiness certificate or the date of issuance of the original export certificate of airworthiness: Do the high and low frequency eddy current inspections within 1,500 flight cycles after the effective date of this AD.
Unsafe condition
This AD was prompted by an analysis which determined that, for certain areas of the fuselage, the current threshold of an Airworthiness Limitations Section inspection is insufficient to detect early crack development. We are issuing this AD to detect and correct cracks in the fuselage skin; such cracking could result in reduced structural integrity of the fuselage.
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