Airworthiness Directive · Amendment 39-18722 · Wings
Fokker Services B.V. Airplanes
This AD applies to all Fokker Services B.V. Model F28 Mark 0070 and 0100 airplanes, certificated in any category.
We are adopting a new airworthiness directive (AD) for all Fokker Services B.V. Model F28 Mark 0070 and 0100 airplanes. This AD was prompted by heavy corrosion found on the wing rear spar lower girder. This AD requires inspections of the affected areas, modification of the wing trailing edge lower skin panels, and corrective actions if necessary. We are issuing this AD to address the unsafe condition on these products.
Within 1,000 flight cycles or 12 months, whichever occurs first after the effective date of this AD, accomplish a one-time detailed visual inspection for corrosion of the wing rear spar lower girder area from WSTA 9270 to 11794, in accordance with Part 1 of the Accomplishment Instructions of Fokker Service Bulletin SBF100-57-049, dated March 24, 2015.
Within 1,000 flight cycles or 12 months, whichever occurs first after the effective date of this AD, modify the wing trailing edge lower skin panels into access panels, in accordance with Part 1 of the Accomplishment Instructions of Fokker Service Bulletin SBF100-57-049, dated March 24, 2015.
Within 2,000 flight cycles or 24 months, whichever occurs first after the effective date of this AD, accomplish a one-time detailed visual inspection for corrosion of the wing rear spar lower girder area from WSTA 2635 to 8700 and WSTA 11794 to 12975, in accordance with Part 2 of the Accomplishment Instructions of Fokker Service Bulletin SBF100-57-049, dated March 24, 2015.
(1) If during any inspection required by paragraph (g) or (i) of this AD, as applicable, corrosion is found, before further flight, remove the corrosion and determine the remaining thickness at the damaged spots, in accordance with the Accomplishment Instructions of Fokker Service Bulletin SBF100-57-049, dated March 24, 2015. If the remaining thickness at the damaged spots, as determined by this paragraph, is not within the tolerances specified in Fokker Service Bulletin SBF100-57-049, dated March 24, 2015, except as required by paragraph (k)(1) of this AD: Before further flight, accomplish the applicable corrective actions as defined in paragraph (j)(1)(i) or (j)(1)(ii) of this AD, as applicable.
(i) For corrosion damage found outboard of WSTA 8200 only: Repair, in accordance with the Accomplishment Instructions of Fokker Service Bulletin SBF100-57-050, Revision 1, dated May 19, 2015.
(ii) 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 Services B.V.'s EASA Design Organization Approval (DOA).
(2) If during any inspection required by paragraph (g) or (i) of this AD, only damage to the surface protection is found, or if the remaining thickness at the damaged spots, as determined by paragraph (j)(1) of this AD, is within the tolerances specified in Fokker Service Bulletin SBF100-57-049, dated March 24, 2015, except as required by paragraph (k)(1) of this AD: Before further flight, restore the surface protection, in accordance with the Accomplishment Instructions of Fokker Service Bulletin SBF100-57-049, dated March 24, 2015, except as required by paragraph (k)(2) of this AD.
(1) Where Fokker Service Bulletin SBF100-57-049, dated March 24, 2015, specifies the acceptability of smaller thickness or customized repairs: Before further flight, obtain acceptable tolerances, using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or Fokker Services B.V.'s EASA DOA.
(2) Where Fokker Service Bulletin SBF100-57-049, dated March 24, 2015, specifies contacting Fokker for a customized repair: Before further flight, repair using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or Fokker Services B.V.'s EASA DOA.
Submit a report of the findings, both positive and negative, of the inspections required by paragraphs (g) and (i) of this AD to Fokker Services, in accordance with the Accomplishment Instructions of Fokker Service Bulletin SBF100-57-049, dated March 24, 2015, at the time specified in paragraph (l)(1) or (l)(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.
