Airworthiness Directive · Amendment 39-18650 · Fuselage
Fokker Services B.V. Airplanes
This AD applies to Fokker Services B.V. Model F28 Mark 0070 and F28 Mark 0100 airplanes, certificated in any category, all serial numbers.
We are adopting a new airworthiness directive (AD) for all Fokker Services B.V. Model F28 Mark 0070 and Mark 0100 airplanes. This AD was prompted by reports of cracking in a certain area of the pressure bulkhead webplate and skin connection angle. This AD requires a one-time inspection of the affected pressure bulkhead webplate and skin connection angle, and corrective actions if necessary. We are issuing this AD to detect and correct cracking of the pressure bulkhead webplate and skin connection angle that could lead to sudden inflight decompression of the airplane, resulting in injury to occupants.
At the time specified in paragraph (h) of this AD: Do a detailed inspection of the pressure bulkhead webplate and skin connection angle on the right-hand side at station 14911 (for Model F28 Mark 0100 airplanes) or station 12447 (for Model F28 Mark 0070 airplanes) at stringer 67 of fuselage section 2, as applicable, in accordance with the Accomplishment Instructions of Fokker Service Bulletin SBF100-53-128, dated November 12, 2014. This AD does not require action for airplanes which, as of the effective date of this AD, have accumulated less than 30,000 flight cycles.
(1) If any crack is found in the skin connection angle, before further flight, repair the skin connection angle, in accordance with the Accomplishment Instructions of Fokker Service Bulletin SBF100-53-129, dated February 16, 2015.
(2) If any crack is found in the pressure bulkhead webplate, before further flight, repair the pressure bulkhead webplate, in accordance with the Accomplishment Instructions of Fokker Service Bulletin SBF100-53-129, dated February 16, 2015.
At the applicable time specified in paragraph (h)(1) or (h)(2) of this AD, do the actions required by paragraph (g) of this AD.
(1) For airplanes that have accumulated less than 40,000 total flight cycles as of the effective date of this AD, do the actions in paragraph (g) of this AD within 2,000 flight cycles after the effective date of this AD.
(2) For airplanes that have accumulated 40,000 or more total flight cycles as of the effective date of this AD, do the actions in paragraph (g) of this AD within 750 flight cycles after the effective date of this AD.
Submit a report of the findings (both positive and negative) of the inspection required by paragraph (g) of this AD to Fokker Services B.V. Engineering, Quality Department P.O. Box 1357, 2130 EL Hoofddorp, the Netherlands; telephone +31 (0)88-6280-350; fax +31 (0)88-6280-111; email technicalservices@fokker.com; Internet http://www.myfokkerfleet.com, in accordance with the Accomplishment Instructions of Fokker Service Bulletin SBF100-53-128, dated November 12, 2014, at the applicable time specified in paragraph (i)(1) or (i)(2) of this AD. The report must include the inspection results; the airplane serial number; the total number of flight cycles and flight hours on the airplane; a sketch or photo to show the location of the crack(s) and damaged part(s), if applicable; and the length of each crack, if applicable.
(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.
