AD/P68/43 Amdt 4 - Wing and Airframe - Fatigue Life Limit

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Legislation au F2006B05370 Not in force Legislative Instrument

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AIRWORTHINESS DIRECTIVE


For the reasons set out in the background section, the CASA delegate whose signature appears below revokes Airworthiness Directive (AD) AD/P68/43 Amdt 3 and issues the following AD under subregulation 39.1 (1) of CASR 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.


 

Partenavia P68 Series Aeroplanes

 

AD/P68/43

Amdt 4


Wing and Airframe - Fatigue Life Limit 11/2003

DM

 

 

Applicability: All Model P68 Series aircraft.

 

Requirement: 1. Inspect the wing and stabilator structures in accordance with Vulcanair Service Bulletin No. 120; and,

 

2.         For the remainder of the airframe:

 

  1. Retire from service; or,

 

b.        Inspect in accordance with a structural inspection program approved by the Authority. (see Note 3).

 

Note 1: In addition to the standard Australian Major Defect Report (required by CAR 52), any cracking discovered should also be reported to the Italian ENAC in accordance with Requirement document Section (E). ENAC contact details: email:seg.dpa@enac.rupa.it or by post: Dipartmento Amministrazione c/o Emilia Chiavarelli, Via di Villa Ricotti 42-0061, Roma, Italy.

 

Note 2: If the wing front spar lower cap and wing rear spar lower cap are to be replaced, it may be an opportune time to install the modifications referred to in AD/P68/22.

 

Note 3: For the purposes of requirement 2.b.of this directive, applications for approval of proposed structural inspection programs may be submitted to the Authority through a District Office. To receive approval, a structural inspection program must comply with the requirements of CAO 101.22 paragraph 3.61(3), FAR 23.573, or an agreed equivalent standard. Information regarding the existence of approved structural inspection programs may be available through CASA district offices.

 

Note 4: ENAC AD 2003-177 refers.

 

Compliance: For Requirement 1:

 

Aircraft with less than 8,500 total flight hours at the effective date of this Directive:

 

Before accumulating 8,500 total flight hours, or within 2 months after the effective date of this Directive, whichever occurs later; unless the initial inspection is already accomplished. Inspect thereafter at intervals not to exceed 500 flight hours.

 

Aircraft with more than 8,500 total flight hours at the effective date of this Directive:

 

Within 50 flight hours or 2 months after 2 October 2003, whichever occurs first; unless the initial inspection is already accomplished. Inspect thereafter at intervals not to exceed 500 flight hours.

 

Note 5: If replacement of the affected wing structure with its wing to fuselage attachments, and/or replacement of the stabilator structure is accomplished, inspection of the replacement structure is not required until the accumulation of 8500 hours component time in service.

 

Note 6: For those aircraft subject to life extension inspection programs pursuant to the previous issue of this directive, the first inspection in accordance with this issue is not required until the next inspection under the previous program falls due after 15 June 2000.

 

2.a.        Retire before 23,660 hours total time in service; or,

 

2.b.       Inspect in accordance with the periods specified in the approved structural inspection programme.

 

The compliance times remain unchanged except for the Requirement 1 repeat inspection interval for aircraft with more than 8,500 total flight hours.

 

This Amendment becomes effective on 24 September 2003.

 

Background: To manage structural fatigue of Partenavia P68 airframe, the previous issue of this directive mandated either retirement, or implementation of a validated structural inspection program for the wing and associated structure, and either inspection or retirement at a safe service life limit for the remaining airframe structure.

 

Amendment 1, effective 15 June 2000, changed the method of control for the wing by implementing a repetitive inspection program, which was prescribed by the RAI, the Italian airworthiness authority. The inspections now include the stabilator.

 

As the fatigue characteristics of the remainder of the airframe have not yet been analysed, this Authority continues to impose a life limit on the remaining airframe. The life is unchanged from the previous issue of this directive.

 

Amendment 2, effective 20 February 2003, added contact details of the Italian Authority, for the reporting of any cracking detected during inspections called out by this Directive. The technical content and compliance times were not changed.

 

Amendment 3, effective 2 October 2003, expanded applicability to all aircraft, and introduced a new Vulcanair service bulletin as the Requirement document for the wing and stabilator structures inspection.

 

Amendment 4 is issued to correct the Requirement 1 repeat inspection interval for aircraft with more than 8,500 total flight hours.

 

The original issue of this Airworthiness Directive became effective on 26 March 1998.


David Villiers

Delegate of the Civil Aviation Safety Authority 15 September 2003

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 


The above AD is notified in the Commonwealth of Australia Gazette on 24 September 2003.

Overview

The Civil Aviation Safety Authority (CASA) issued Airworthiness Directive (AD) AD/P68/43 Amdt 4 in 2003 under subregulation 39.1(1) of the Civil Aviation Safety Regulations 1998 (CASR 1998). This AD specifically applies to all Model P68 Series aircraft and was enacted to address safety concerns related to structural fatigue, particularly in the wing and stabilator structures of these aircraft. The policy objective is to ensure the airworthiness of these aircraft by mandating inspections or retirement of the affected components at specified intervals to prevent unsafe conditions due to fatigue. The directive requires inspections of the wing and stabilator structures in accordance with a specified service bulletin and mandates either retirement or inspection of the remaining airframe structure at particular intervals or service life limits, with detailed compliance timelines provided. This legislative instrument aims to maintain the highest safety standards in civil aviation by ensuring that all aircraft meet the necessary airworthiness criteria through regular and rigorous inspections or appropriate life-limiting measures.

Scope and Application

The Airworthiness Directive (AD) AD/P68/43 Amdt 4 applies to all Model P68 Series aircraft and mandates specific actions to ensure their airworthiness, focusing on fatigue life limits of the wing and airframe structures. The directive applies nationally within the Commonwealth of Australia and is issued under subregulation 39.1(1) of the Civil Aviation Safety Regulations 1998. The AD requires that specific inspections and actions be undertaken on the aircraft's wing and stabilator structures, with further instructions to either retire the airframe from service or conduct inspections in accordance with a structural inspection program approved by the Civil Aviation Safety Authority (CASA). Compliance with these directives must be achieved within specified timeframes, depending on the aircraft's total flight hours. The directive includes provisions for reporting any discovered cracking to the Italian Civil Aviation Authority (ENAC), and allows for certain modifications to be implemented concurrently with required inspections. Exemptions or variations to the AD may be addressed through subordinate instruments or specific approvals granted by CASA, though the primary directive remains clear and mandatory for all affected aircraft within Australia's jurisdiction.

Key Provisions

The Airworthiness Directive (AD) AD/P68/43 Amdt 4, issued under subregulation 39.1(1) of the Civil Aviation Safety Regulations 1998 (CASR 1998), applies to all Model P68 Series aircraft (Applicability). This AD mandates specific actions to ensure the airworthiness of these aircraft. For the wing and stabilator structures, inspections must be conducted in accordance with Vulcanair Service Bulletin No. 120 (Requirement 1). For the rest of the airframe, two options are provided: either the aircraft must be retired from service before reaching 23,660 hours total time in service, or it must be inspected in accordance with an approved structural inspection program (Requirement 2). Compliance with the directive varies depending on the total flight hours of the aircraft at the effective date of the directive. For aircraft with less than 8,500 total flight hours at the effective date, inspections must be completed before accumulating 8,500 total flight hours or within two months after the effective date, whichever occurs later. Aircraft with more than 8,500 total flight hours must be inspected within 50 flight hours or two months after 2 October 2003, whichever occurs first (Compliance). Repeat inspections must be conducted at intervals not exceeding 500 flight hours. The AD imposes specific obligations on the operators of Partenavia P68 Series aircraft. Operators must ensure that their aircraft comply with the inspection requirements set out in the AD. For the wing and stabilator structures, this involves conducting inspections as per Vulcanair Service Bulletin No. 120. For the remainder of the airframe, operators must either retire the aircraft before it reaches 23,660 hours total time in service or ensure that it is inspected in accordance with an approved structural inspection program. Additionally, any cracking discovered during inspections must be reported to the Italian ENAC as specified in Note 1 of the AD. Operators must also ensure that if the wing front spar lower cap and wing rear spar lower cap are replaced, any modifications referred to in AD/P68/22 are installed (Note 2). Failure to comply with the AD may result in civil or criminal consequences. The AD does not explicitly state penalties for non-compliance, but it is issued under the authority of the Civil Aviation Safety Regulations 1998, which allows for enforcement actions, including fines and imprisonment, for violations of airworthiness directives. Non-compliance with the AD could potentially lead to the grounding of the affected aircraft, which would have significant operational and financial implications for the operators. Furthermore, failure to report any cracking discovered during inspections to the Italian ENAC as required by Note 1 could result in additional regulatory scrutiny and penalties from the relevant authorities.

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