Airworthiness Directive · Amendment 39-17819 · Fuselage
Fokker Services B.V. Airplanes
This AD applies to Fokker Services B.V. Model F.28 Mark 0070 and 0100 airplanes, certificated in any category, as identified in Fokker Service Bulletin SBF100-53-118, Revision 2, dated October 16, 2012.
We are adopting a new airworthiness directive (AD) for certain Fokker Services B.V. Model F.28 Mark 0070 and 0100 airplanes. This AD was prompted by an evaluation by the design approval holder (DAH) indicating that the butt-joints on the forward fuselage above the passenger door are subject to widespread fatigue damage (WFD). This AD requires inspecting the forward fuselage butt-joints for cracking, repairing any crack, and eventually doing a terminating repair. We are issuing this AD to prevent fatigue cracking of such butt-joints, which could result in reduced structural integrity of the airplane and in- flight decompression of the airplane.
Before the accumulation of 35,000 total flight cycles, or within 8 months after the effective date of this AD, whichever occurs later: Do a low frequency eddy current inspection for cracking of the forward fuselage butt-joints, in accordance with the Accomplishment Instructions of Fokker Service Bulletin SBF100-53-118, Revision 2, dated October 16, 2012.
If any cracking is found during the inspection specified in paragraph (g) of this AD, before further flight, do the actions specified in paragraph (h)(1) or (h)(2) of this AD.
(1) Accomplish a temporary repair, including a detailed inspection for cracks in the butt strap on the inside of the applicable joint, and all applicable corrective actions, in accordance with the Accomplishment Instructions of Fokker Service Bulletin SBF100-53-118, Revision 2, dated October 16, 2012.
(2) Do a terminating repair of the forward fuselage butt-joints, including a detailed inspection for cracks in the butt strap on the inside of the applicable joint, and all applicable corrective actions, in accordance with the Accomplishment Instructions of Fokker Service Bulletin SBF100-53-119, Revision 2, dated May 8, 2013. Accomplishing the terminating repair specified in this paragraph is a method of compliance with the terminating repair required by paragraph (j) of this AD.
Submit a report of any crack findings from the inspection specified in paragraph (g) of this AD to Fokker Services, Hoeksteen 40, 2132 MS Hoofddorp, P.O. Box 1357, 2130 EL Hoofddorp, The Netherlands; by using the Reporting Form (figure 14 and figure 15, as applicable) of Fokker Service Bulletin SBF100-53-118, Revision 2, dated October 16, 2012; at the applicable time specified in paragraph (i)(1) or (i)(2) of this AD.
(1) If the inspection was done on or after the effective date of this AD: Submit the report within 30 days after the inspection.
(2) If the inspection was done before the effective date of this AD: Submit the report within 30 days after the effective date of this AD.
Before the accumulation 50,000 total flight cycles, or within 8 months after the effective date of this AD, whichever occurs later: Do the terminating repair of the forward fuselage butt-joints, including a detailed inspection for cracks in the butt strap on the inside of the applicable joint, and all applicable corrective actions, in accordance with the Accomplishment Instructions of Fokker Service Bulletin SBF100-53-119, Revision 2, dated May 8, 2013. Do all applicable corrective actions before further flight.
