Document ID: chunk:federal_register_of_legislation:F2006B09703:body:0
Version: federal_register_of_legislation:F2006B09703
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COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
    SCHEDULE OF AIRWORTHINESS DIRECTIVES

    Fokker F27 Series Aeroplanes

AD/F27/136 Outer Flap Centre Hinge 9/94

    Applicability: Fokker Model F27 aircraft, serial numbers 10102 and 10105 to 10240 inclusive.

               Requirement: Conduct a High Frequency Eddy Current (HFEC) inspection of the outer flap centre hinge bearing bore, on both wings, in accordance with Part 1 of Fokker Service Bulletin (SB) F27/57-66. Repair flap centre hinge fittings whether cracked or not.

               Note: RLD AD 91-129 refers.

    Compliance: 1. Hinge fittings not modified in accordance with Fokker SB F27/57-22.

                   1. Inspect per Fokker SB F27/57-66 part 1

(i)       If the aircraft has exceeded 72000 flights, then inspect within 1000 flights from 18 August 1994 or before 1 February 1995, whichever occurs first.

                  b.    Repair per Fokker SB F27/57-66 part 2

(i)       Within 300 flights if the crack length inside the bore is less than 5mm and no cracking exists on the faces of the bore,

                     (ii)     Before further flight if cracking exceeds either of the limitations of para
                     1.b. (i).

                     (iii)  Within 2800 flights or two years if no cracks are found.

                 2.    Hinge fittings modified in accordance with Fokker SB F27/57-22.

                   1. Inspect per Fokker SB F27/57-66 part 1

(i)       If the aircraft has exceeded 55000 flights, then inspect within 1000 flights from 18 August 1994 or before 1 February 1995, whichever occurs first.

                  b.    Repair per Fokker SB F27/57-66 part 2

(i)       Within 300 flights if the crack length inside the bore is less than 5mm and no cracking exists on the faces of the bore,

(ii)     Before further flight if cracking exceeds either of the limitations of para 2.b.(i), or if a crack inside the bore is located near the grease nipple bore.

                     (iii)  Within 2800 flights or two years if no cracks are found.

               Note: Outer flap centre hinges which have not yet reached the newly established retirement lives of 72000 or 55000 flights are covered by the F27 Structural Integrity Program, Part 1, Item 57-50-02 (AD/F27/103 refers).
 COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
 SCHEDULE OF AIRWORTHINESS DIRECTIVES

           Background:  Analysis of the service loads spectrum has shown that the loads on the outer flap centre hinge are higher than originally expected. This has resulted in a reduction in the fatigue life for the early style hinge fittings. This Directive requires inspection and repair to maintain airworthiness integrity on affected aircraft which now find themselves in excess of the new hinge fitting retirement lives.