Document ID: chunk:federal_register_of_legislation:F2021L01010:body:0:p2
Version: federal_register_of_legislation:F2021L01010
Segment Type: other
Provision Reference: 
Character Range: 2804–4394

2. Before further flight.
                    3. At intervals not to exceed 200 hours TIS. If cracks are found during any inspection, incorporate Kit No. 101-8030-1 S or Kit No. 114-8015-1 S, as applicable.

             Note 3: If the aircraft is on the manufacturer's maintenance schedule then a planning tolerance of ± 10% can be applied to the 200 hour TIS periods detailed in Requirements 1 and 3 of this AD as provided in the manufacturer's phase inspection schedules.
             This AD commences on 17 August 2021.
Background:  The manufacturer required a mandatory inspection of the nose gear lower shock absorber for evidence of slippage at the intersection of the tube and fork assembly, and a dye check of the weld area on the fork assembly.
             Amendment 2 introduced a modification kit which, if fitted, removes the repetitive inspection requirement.
             Amendment 3 required the same inspection requirements by a different inspection method but required incorporation of an improved nose landing gear fork kit anytime crack is found; and added additional aircraft to applicability.
             Amendment 4 was issued on 26 October 2006 and corrected an error in Requirement 3, where Part III of the referenced Beech MSB should have been Part II. This error flowed from related FAA AD 2004-23-02.
             Amendment 5 introduces a planning tolerance to align the inspections required with the aircraft phase inspection schedule detailed in the aircraft maintenance manual.

David Punshon
Delegate of the Civil Aviation Safety Authority
16 July 2021