Document ID: chunk:federal_register_of_legislation:F2022L00686:body:0:p1
Version: federal_register_of_legislation:F2022L00686
Segment Type: other
Provision Reference: 
Character Range: 0–2979

AIRWORTHINESS DIRECTIVE
On the commencement date specified below, and for the reasons set out in the background section, the CASA delegate whose signature appears below repeals Airworthiness Directive (AD) AD/BEECH 55/79 Amdt 3 and issues the following AD under subregulation 39.001 (1) of CASR and subsection 33 (3) of the Acts Interpretation Act 1901. The AD requires that the action set out in the requirement section (being action that the delegate considers necessary to correct an 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.

Textron Aviation (Beechcraft) 55, 58 and 95-55 (Baron) Series Aeroplanes
AD/BEECH 55/79 Amdt 4  Wing Bolt, Nut and Fitting  10/2022

Applicability:  All models of Textron Aviation (Beechcraft) 55, 58 and 95-55 series aircraft.
Requirement:       1. Remove and inspect the wing bolts, washers, nuts and fittings in accordance with Beechcraft Baron Shop Manual 55-590000-13 Revision E17, Section 3, for model 55 and 58 series; or Baron Maintenance Manual 102- 590000-5 Revision A23, Section 57-00-00, for model 58P and TC series, both as in force on the date of commencement of this AD.
                   2. Retire wing bolts, washers and nuts from service and replace with new hardware in accordance with Beechcraft Baron Shop Manual 55-590000-13 Revision E17 Section 3 or Baron Maintenance Manual 102-590000-5 Revision A23 Section 57-00-00 as applicable, both as in force on the date of commencement of this AD. Render unserviceable all hardware retired.
                Note 1:  The bolt torque should be checked before removal for inspection or replacement to confirm the bolt has been torqued to correct value. If the torque value is incorrect, other maintenance action may be required.
Compliance:          1. a. Unless inspection has already been accomplished in accordance with either of the requirement documents within 60 months from the initial installation of the wing bolts, inspect within 100 hours time in service (TIS) or two months from the commencement date of this AD, whichever occurs first.
                     b. Re-inspect at intervals not to exceed 60 months from the previous inspection.
                2. Before 15 years (180 months) TIS after initial installation of the wing bolts.
                This AD commences on 10 May 2022.
Background:     The initial issue of this Airworthiness Directive became effective on 1 February 1996 and made mandatory the inspection and replacement periods for the wing attachment hardware as detailed in the requirement document.
                Amendment 1 of this AD updated the revision status of the Beech 55 Shop Manual.
                Amendment 2 of this AD added the Note to Requirement 2 and added