Document ID: chunk:federal_register_of_legislation:F2006L03618:body:0:p1
Version: federal_register_of_legislation:F2006L03618
Segment Type: other
Provision Reference: 
Character Range: 0–3128

AIRWORTHINESS DIRECTIVE
On the effective date specified below, and for the reasons set out in the background section, the CASA delegate whose signature appears below revokes Airworthiness Directive (AD) AD/F50/96 and issues the following AD under subregulation 39.001(1) of CASR 1998.  The AD requires that the action set out in the requirement section (being action that the delegate considers necessary to correct the unsafe condition) be taken in relation to the aircraft or aeronautical product mentioned in the applicability section: (a) in the circumstances mentioned in the requirement section; and (b) in accordance with the instructions set out in the requirement section; and (c) at the time mentioned in the compliance section.

Fokker F50 (F27 Mk 50) Series Aeroplanes
AD/F50/96 Amdt 1  Bottom Skin Chine Line  12/2006

Applicability:  Model F27 Mark 050 aircraft, serial numbers 20103 through 20172.
Requirement:       1. Visually inspect the Fuselage Bottom Skin Chine Line between Fuselage Station (STA) 6675 and STA 15375 in accordance with Part 3, Steps A and B of the Accomplishment Instructions of Fokker Services Service Bulletin
                   SBF50-53-058, dated 30 June 2006, or later EASA approved revision.

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

                     If the crack length is more than 50 mm, before further flight, remove the paint in accordance with AMM Chapter 51-24-00 and reinspect.

                     If the crack length is between 10 and 50 mm, within 50 flight cycles, remove the paint in accordance with AMM Chapter 51-24-00, and reinspect.

                     If the crack length is less than 10 mm, within 1,000 flight cycles, eddy-current inspect in accordance with Fokker SBF50-53-059. dated
                     24 August 2006, or later EASA approved revision.

                     b. When cracks are found after the removal of paint as instructed by Requirement 1.a., proceed in accordance with the instructions in
                     SBF50-53-058, and within 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 between 10 mm and 50 mm, repeat the visual inspection in accordance with SBF50-53-058 within 100 flight cycles after the initial inspection, and thereafter at intervals not to exceed 100 flight cycles; until accomplishment of SBF50-53-059.

                     If the crack length is less than 10 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