Airworthiness Directive AD/BEECH 55/79 Amdt 7

Full document text

COMMONWEALTH OF AUSTRALIA Civil Aviation Safety Regulations 1998 CIVIL AVIATION SAFETY AUTHORITY Regulation 39.001 Page 1 of 4 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 6 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 7 Wing Bolt, Nut and Fitting 12/2025 Applicability: All models of Textron Aviation (Beechcraft) 55, 58 and 95-55 series aircraft. Requirement: 1. Remove inspection covers from wing attach fitting recesses and inspect for corrosion or loss of inhibitor. Also inspect drain holes for any blockage that would cause water or debris to accumulate. Note 1: It may be necessary to use a bright light and mirror/magnifying glass to see hard to view areas of the bolt or fittings for signs of corrosion on accessible areas of the bolt. Non accessible areas like the bolt thread encapsulated by the nut will be inhibited, so it is highly unlikely they will experience corrosion unless the general surrounding area is corroded. 2. Remove and inspect wing bolts, washers, nuts and fittings in accordance with: • Beechcraft Baron Maintenance Manual 55-590000-13 Revision H2 Revision date May 29, 2024, Section 57-10-00, for model 55 and 58 series; or • Baron Maintenance Manual 102-590000-5 Revision A25, Revision date June 01, 2002, Section 57-00-00, for model 58P and TC series; both as in force on the date of commencement of this AD. Note 2: 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. 3. Retire wing bolts, washers and nuts from service and replace with new hardware in accordance with: • Beechcraft Baron Maintenance Manual 55-590000-13 Revision H2 Revision date May 29, 2024, Section 57-10-00, for model 55 and 58 series; or • Baron Maintenance Manual 102-590000-5 Revision A25, Revision date June 01, 2002, Section 57-00-00, for model 58P and TC series; both as in force on the date of commencement of this AD. Render unserviceable all hardware retired. Alternatively for Model 55 and 58 series aircraft only, the bolts may be maintained on condition IAW Table 201, Beechcraft Baron Maintenance Manual 55-590000-13 Revision H2 Revision date May 29, 2024, Section 57-10-00, as in force on the date of commencement of this AD. COMMONWEALTH OF AUSTRALIA Civil Aviation Safety Regulations 1998 CIVIL AVIATION SAFETY AUTHORITY Regulation 39.001 Textron Aviation (Beechcraft) 55, 58 and 95-55 (Baron) Series Aeroplanes AD/BEECH 55/79 Amdt 7 (continued) Page 2 of 4 Compliance: For Requirement 1: Every 12 calendar months for all aircraft. If visible corrosion is found within the recess or on visible portion of the bolt or nuts, washers or fittings, then Requirement 2 must be accomplished before further flight. For Requirement 2: a. For aircraft operating only in private operations: i. unless the inspection has already been accomplished in accordance with either the Beechcraft Baron Maintenance Manual 55-590000-13 Revision H2 dated May 29, 2024 or the Baron Maintenance Manual 102-590000-5 Revision A25 dated June 1, 2002, each as in force at the commencement of this AD (the requirement documents) within 10 years from the initial installation of the wing bolts — inspect within 100 hours’ time in service (TIS) or 12 months from the commencement date of this AD, whichever occurs first. Note 4: Installation of the wing bolts includes where they are removed for inspection purposes and re-installed. ii. re-inspect at intervals not to exceed 10 years from the previous inspection. b. For all other operational categories: i. unless the inspection has already been accomplished in accordance with either of the requirement documents within 5 years from the installation of the wing bolts — inspect within 100 hours’ TIS or 12 months from the commencement date of this AD, whichever occurs first. Note 5: Installation of the wing bolts includes where they are removed for inspection purposes and re-installed. ii. re-inspect at intervals not to exceed 5 years from the previous inspection. For Requirement 3: a. For models 55 and 58 series aeroplanes - Before 20 years TIS after the first installation of new zero time wing bolts. b. For models 58P and 58TC series aeroplanes - Before 15 years TIS after the first installation of new zero time wing bolts. Alternatively for Model 55 and 58 series aircraft only, the bolts may be maintained on condition IAW Table 201, Beechcraft Baron Maintenance Manual 55-590000-13 Revision H2 Revision date May 29, 2024, Section 57-10-00, as in force on the date of commencement of this AD. Note 6: Always replace wing attach nuts with new items when removing the wing attach bolts for inspection. COMMONWEALTH OF AUSTRALIA Civil Aviation Safety Regulations 1998 CIVIL AVIATION SAFETY AUTHORITY Regulation 39.001 Textron Aviation (Beechcraft) 55, 58 and 95-55 (Baron) Series Aeroplanes AD/BEECH 55/79 Amdt 7 (continued) Page 3 of 4 Mandatory reporting requirements: Both NIL findings of defects and confirmed defects for Requirement 2 inspection must be reported via CASA’s Defect Reporting Service, either through the online portal at: