AIRWORTHINESS DIRECTIVE
For the reasons set out in the background section, the CASA delegate whose signature appears below revokes Airworthiness Directive (AD) AD/BEECH 55/61 Amdt 1 and issues the following AD under subregulation 39.1 (1) of CAR 1998. The AD requires that the action set out in the requirement section (being action that the delegate considers necessary to correct the 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.
Beechcraft 55, 58 & 95-55 (Baron) Series Aeroplanes
AD/BEECH 55/61
Amdt 2
Wing Fatigue Life Limitation 3/2003
Applicability: All models 58, 58A, 58TC, 58P and 58PA series.
Requirement: Retire the wing spar and wing centre section spar low cap (and associated structural fittings) together with the wing rear spar upper and lower attachment fitting assemblies.
The model 58TC and 58P life limitation assumes an average mean cruise weight of 2490kg and one landing every 40 minutes. Should the mean cruise weight be greater than 2540kg or should the landings occur at a greater frequency than one landing every 30 minutes the Authority must be advised as it will be necessary to reassess the life limitation.
Note 1: The wing rear spar attachment fitting assembly includes both fuselage and wing fitting components.
Note 2: On the basis of currently available fatigue substantiating data, only one spar cap replacement is permitted. This will allow a single lifetime extension from spar cap replacement.
Note 3: For aircraft which have had winglets fitted subsequent to manufacture, the retirement life, in hours, is to be calculated using the formula;
Retirement Life Formula: RL = A + RLW ( 1 - A )
RLW/O
Where:
RL = Retirement Life (Hours)
A = Hours flown before winglets were fitted
RLW = Retirement Life (Hours) with winglets fitted RLW/O= Retirement Life (Hours) without winglets fitted
Beechcraft 55, 58 & 95-55 (Baron) Series Aeroplanes
AD/BEECH 55/61 Amdt 2 (Continued)
The Value for RLW will need to be specified based on approved data from the Supplemental Type Certificate Holder or, in the absence of such data, the value selected shall be approved by the Civil Aviation Safety Authority.
Compliance: 1. For models 58 and 58A series: before exceeding 16,000 hours’ time in service or if winglets were installed, retirement life is in accordance with the Retirement Life Formula specified in this AD.
2. For model 58TC series: before exceeding 10,000 hours’ time in service, or if winglets were installed, retirement life is in accordance with the Retirement Life Formula specified in this AD.
3. For models 58P and 58PA series: before exceeding 13,250 hours’ time in service, or if winglets were installed, retirement life is in accordance with the Retirement Life Formula specified in this AD.
This Amendment becomes effective on 20 March 2003.
Background: Analysis and fatigue tests by the manufacturer have established the above retirement lives for the wing main spar and associated structure. Amendment 1 clarified the intent that the applicability includes all pressurised Baron aircraft.
This Amendment adds a formula to calculate the wing structure retirement life for aircraft that have had winglets installed since the aircraft was manufactured.
Amendment 1 of this Airworthiness Directive became effective on 30 November 2000.
This original issue of this Airworthiness Directive became effective on 31 March 1981.
David Alan Villiers
Delegate of the Civil Aviation Safety Authority 14 January 2003
The above AD is notified in the Commonwealth of Australia Gazette on 26 February 2003.
Overview
The Civil Aviation Safety Authority Act 1998, enacted in 1998, established the framework for ensuring the safety of civil aviation in Australia. This legislation enabled the Civil Aviation Safety Authority (CASA) to issue Airworthiness Directives (ADs) to address specific safety concerns or conditions in aircraft, as demonstrated by the AD/BEECH 55/61 Amdt 2 issued under this Act. This particular AD aims to mitigate the identified risk of wing fatigue in certain models of the Beechcraft 55, 58 and 95-55 (Baron) series aeroplanes by mandating the retirement of specific wing components based on service hours and flight conditions. The objective of this policy is to ensure the continued airworthiness and safety of these aircraft by addressing structural integrity issues that could potentially compromise flight safety.
Scope and Application
This Airworthiness Directive (AD) applies to all models of the Beechcraft 55, 58 and 95-55 (Baron) series aeroplanes, specifically those designated as 58, 58A, 58TC, 58P, and 58PA. The AD mandates the retirement of certain wing spar and attachment components to address a safety concern identified by the manufacturer through analysis and fatigue tests. The requirement applies to aircraft based in Australia and is overseen by the Civil Aviation Safety Authority (CASA). The AD specifies compliance timelines, including certain hour thresholds for each model series, and provides a formula for calculating the retirement life of wing structures on aircraft that have had winglets installed after their manufacture. The AD does not specify exclusions or exemptions, and its application is broad across the designated aircraft models within the Commonwealth of Australia. Subordinate instruments may further define specific procedures or technical details related to the implementation of this AD.
Key Provisions
The Airworthiness Directive AD/BEECH 55/61 Amdt 2, issued under subregulation 39.1(1) of the Civil Aviation Regulations 1998 (CAR 1998), applies to all models of the Beechcraft 55, 58, and 95-55 (Baron) series aeroplanes. This directive mandates the retirement of specific wing components, namely the wing spar and wing centre section spar low cap along with their associated structural fittings and the wing rear spar upper and lower attachment fitting assemblies. The requirement to retire these components is contingent on the aircraft reaching a certain number of flight hours or if winglets have been fitted post-manufacture. For models 58 and 58A, the directive applies before exceeding 16,000 flight hours or according to a specified formula if winglets are installed. For model 58TC, the limit is before 10,000 flight hours or according to the formula if winglets are installed. For models 58P and 58PA, the directive applies before 13,250 flight hours or according to the formula if winglets are installed.
The AD imposes specific obligations on the parties governed by it. Aircraft operators must ensure that the mandated components are retired in accordance with the instructions and timelines specified in the directive. This includes adhering to the stipulated flight hour limits and using the provided formula for calculating the retirement life for aircraft fitted with winglets. Operators must also notify the Civil Aviation Safety Authority (CASA) if the average mean cruise weight exceeds 2540kg or if the landing frequency is more than one landing every 30 minutes, as these conditions necessitate a reassessment of the life limitation. Furthermore, if winglets have been added post-manufacture, operators must use the retirement life formula provided in the directive to calculate the appropriate retirement life for the wing structure.
Failure to comply with the requirements of this Airworthiness Directive may result in significant consequences. While the directive does not explicitly state offences or penalties, non-compliance with such directives typically leads to enforcement actions by CASA, which can include fines, suspension of airworthiness certificates, or other regulatory actions under the Civil Aviation Act 1988 and the Civil Aviation Regulations 1998. These penalties can be severe, both financially and operationally, underscoring the importance of adhering to the specified requirements.