Document ID: chunk:federal_register_of_legislation:F2006L03618:body:0:p2
Version: federal_register_of_legislation:F2006L03618
Segment Type: other
Provision Reference: 
Character Range: 2854–6092

mm, within 1,000 flight cycles, eddy-current inspect in accordance with Fokker SBF50-53-059.
                   2. Visually inspect the Fuselage Bottom Skin Chine Line between STA 1320 and STA 3100, in accordance with Part 3, Steps C and D of the Accomplishment Instructions of SBF50-53-058, dated 30 June 2006, or later EASA approved revision.

                   When cracks are found appearing through the paint layer, proceed in accordance with the instructions in SBF50-53-058 and within the time limits provided in Requirement 1.a.

                   When cracks are found after the removal of paint, proceed in accordance with the instructions in SBF50-53-058 and within the time limits provided in Requirement 1.b.

                   3. In all cases, whether or not cracks were found and repaired in accordance with Requirements 1 and 2 of this Directive, eddy-current inspect the Fuselage Bottom Skin Chine Line (between the same fuselage stations as covered by the visual inspection) in accordance with Part 3, Accomplishment Instructions of
                   SBF50-53-059 dated 24 August 2006, or later EASA approved revision.

                   When cracks are found during the eddy-current inspection, proceed in accordance with the instructions in SBF50-53-059 and the following time limits:

                   If the crack length is more than 100 mm, before further flight, repair in accordance with SRM Chapter 53-00-02 Repair No. 10.

                   If the crack length is between 50 mm and 100 mm, within 50 flight cycles, repair in accordance with SRM Chapter 53-00-02 Repair No. 10.

                   If the crack length is less than 50 mm, within 100 flight cycles after the initial inspection, accomplish the eddy-current inspection in accordance with SBF50-53-059, and repeat thereafter at intervals not to exceed 100 flight cycles; until the repair is accomplished.

                   When cracks are found as a result of the inspection requirements of this Directive, within 7 days after the inspection, report all findings to Fokker Services B.V.

                Note:  CAA-NL AD NL-2006-009 R1 refers.
Compliance:        1. Upon accumulating 20,000 total flight cycles or within 3 weeks after
                   31 August 2006, whichever occurs later.

                   2. Upon accumulating 45,000 total flight cycles or with 3 weeks after
                   31 August 2006, whichever occurs later.

                   3. Within 1,000 flight cycles after the visual inspection in accordance with
                   SBF50-53-058.

             The compliance times for Requirements 1 and 2 remain unchanged by this issue of this Directive.
             This Amendment becomes effective on 23 November 2006.
Background:  The inspection procedure as described by Fokker 50 Non-Destructive Testing Manual (NDTM), Part 6, Chapter 53-30-02, which is referenced by Fokker 50 Maintenance Review Board (MRB) Tasks 530000-00-04 and 530000-00-08 does not show the correct inspection areas.  In addition to the existing procedure, the area at the kink in the bottom fuselage skin, the actual chine line, must be inspected.  Investigation revealed that a number of aircraft have already passed the