Airworthiness Directive · Amendment 39-14737 · Fokker Model F.28 Mark 0070 and 0100 Airplanes
Fokker Model F.28 Mark 0070 and 0100 Airplanes
This AD applies to all Fokker Model F.28 Mark 0070 and 0100 airplanes, certificated in any category.
The FAA is adopting a new airworthiness directive (AD) for all Fokker Model F.28 Mark 0070 and 0100 airplanes. This AD requires a one- time detailed inspection to detect corrosion on the wing rear spar lower girder, and related investigative and applicable corrective actions if necessary. This AD results from reports of corrosion of the wing rear spar lower girder between wing station (STA) 8700 and wing STA 9200. We are issuing this AD to detect and correct corrosion of the wing rear spar lower girder, which could result in reduced structural integrity of the wing rear spar.
You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.
Within 4,000 flight hours or 21 months after the effective date of this AD, whichever occurs first: Do a detailed inspection to detect corrosion on the wing rear spar lower girder between wing STA 8700 and wing STA 9200, and do all related investigative and applicable corrective actions, by accomplishing all the actions specified in the Accomplishment Instructions of Fokker Service Bulletin SBF100-57-038, dated April 15, 2005, except as provided by paragraphs (g) and (h) of this AD. Do all related investigative and corrective actions before further flight. If any damage is found that measures more than or equal to 1.3 millimeters (mm) deep, or if the thickness of the remaining material of the rear spar lower girder is less than or equal to 2.1 mm thick, repair in accordance with a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA) (or its delegated agent).
Note 1: For the purposes of this AD, a detailed inspection is: “An intensive examination of a specific item, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate. Inspection aids such as mirror, magnifying lenses, etc., may be necessary. Surface cleaning and elaborate procedures may be required.”
(g) If, during the accomplishment of the corrective actions required by paragraph (f) of this AD, the service bulletin specifies contacting the manufacturer for certain repair instructions: Before further flight, repair in accordance with a method approved by the Manager, International Branch, ANM-116; or the EASA (or its delegated agent).
Submit a report of the findings (both positive and negative) of the inspection required by paragraph (f) of this AD to Fokker Services B.V., Technical Services Dept., P.O. Box 231, 2150 AE Nieuw-Vennep, the Netherlands; fax +31 252 627211; e-mail Technicalservices.FokkerServices@stork.com; at the applicable time specified in paragraph (h)(1) or (h)(2) of this AD. Use the reporting forms in Figures 3 and 4 of Fokker Service Bulletin SBF100-57-038, dated April 15, 2005. Under the provisions of the Paperwork Reduction Act (44 U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has approved the information collection requirements contained in this AD and has assigned OMB Control Number 2120-0056.
(1) If the inspection was done 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.
