Federal Register of Legislation - Australian Government

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AD/BEECH 76/18 Amdt 2 Airworthiness Directives as made
This instrument repeals and replaces AD/BEECH 76/18 Amdt 1 - MLG "A" Frame Assembly.
Administered by: Infrastructure, Transport, Cities and Regional Development
Exempt from sunsetting by the Legislation (Exemptions and Other Matters) Regulation 2015 s12 item 15
Registered 04 Jun 2019
Tabling HistoryDate
Tabled HR02-Jul-2019
Tabled Senate02-Jul-2019

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 76/18 Amdt 1 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) 76 (Duchess) Series Aeroplanes

AD/BEECH 76/18 Amdt 2

Main Landing Gear “A” Frame Assembly

12/2019

 

Applicability:

Textron Aviation Beechcraft model 76 aircraft with serial numbers ME-1 through ME-437, that do not have a main landing gear (MLG) “A” frame assembly installed with both part numbers (P/N) 105-810023-83 (left) and P/N 105-810023-84 (right).

Requirements:

1.    Inspect, using both visual and magnetic particle methods, both the left and right MLG “A” frame assemblies for cracks in accordance with the Accomplishment Instructions section of Textron Aviation Beechcraft mandatory Service Bulletin (SB) 32-4156 dated 3 May 2019, as in force at the date of issue of this AD, paying particular attention to the tips of the gussets and the small corrosion treatment hole adjacent to the gusset.

2.    If a crack is detected in any MLG “A” frame assembly, before further flight, replace the assembly with one of the following in accordance with Chapter 32 of the Duchess Model 76 Maintenance Manual, as in force at the date of issue of this AD:

(a)   a new MLG “A” frame assembly with the same P/N as that found cracked.

Note:  The 100 hours’ time in service or 12 month repetitive inspection requirement of the MLG “A” frame assembly expressed below is not affected if a new MLG “A” frame is installed.

(b)   a P/N 105-810023-83 (left) or P/N 105-810023-84 (right) MLG “A” frame assembly, as applicable. Repetitive inspections are no longer required on an MLG “A” frame assembly incorporating this design configuration.

Note:  United States Federal Aviation Administration (FAA) AD 97-06-10 Amdt 39‑9967 refers (and references now superseded Textron Aviation Beechcraft SB 2361 Revision III).

Compliance:

Within 100 hours’ time in service or 12 months, whichever occurs first, after 23 May 2019, and thereafter at intervals not to exceed 100 hours’ time in service or 12 months, whichever occurs first, until both P/N 105-810023-83 and P/N 105‑810023-84 MLG “A” frame assemblies are installed.

 

This AD commences on 7 June 2019.

Background:

The FAA has received reports of fatigue cracks developing on the main landing gear “A” frame assembly of Textron Aviation Beechcraft Model 76 aircraft. These cracks, if not detected and corrected, would cause the main landing gear to collapse.

 

Amendment 2 of this AD is issued in response to the cancellation of Textron Aviation Beechcraft mandatory SB 2361 Revision III and its replacement by Textron Aviation Beechcraft mandatory SB 32-415. It is unknown at this time if the FAA will cancel FAA AD 97-06-10 and issue a new AD or issue an Alternate Means Of Compliance (AMOC) for the use of mandatory SB 32-4156.  AD/BEECH 76/18 Amdt 2 is issued to ensure industry comply with the current applicable document, Mandatory SB 32‑4156, which requires the use of magnetic particle inspection instead of a dye penetrant inspection.

Amendment 1 of this AD was issued in response to a new FAA AD which introduced terminating action for the repetitive inspection requirement of this directive if certain improved design “A” frame assemblies are installed.

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Pieter van Dijk
Delegate of the Civil Aviation Safety Authority

31 May 2019