Airworthiness Directive · Amendment 39-18771 · Fuselage
Fokker Services B.V. Airplanes
This AD applies to Fokker Services B.V. Model F28 Mark 0100 airplanes, certificated in any category, serial numbers 11244 through 11407 inclusive.
We are adopting a new airworthiness directive (AD) for certain Fokker Services B.V. Model F28 Mark 0100 airplanes. 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. This AD requires one time high and low frequency eddy current inspections of the affected fuselage skin for cracks, and repair if necessary. We are issuing this AD to address the unsafe condition on these products.
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.
If any crack is found during any inspection required by paragraph (g) of this AD: Before further flight, repair using a method approved by the Manager, International Branch, ANM 116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Fokker B.V. Service's EASA Design Organization Approval (DOA).
