COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
Piper PA-32 (Cherokee Six) Series Aeroplanes
AD/PA-32/42
Amdt 1
Wing Structural Fatigue Life Limitation 13/96
Applicability: All PA-32 series aircraft, all models. Requirement: 1. Retire from service:
1.1. The wing main spar assembly; and
1.2. The bottom cap of the wing main spar box (carry through). OR
2. Inspect the lower wing joint for fatigue cracks in accordance with an inspection program approved through a District Office of the Authority.
Note 1: For Requirement 1, replace retired components in accordance with approved maintenance data; Regulations 42V and 2A refer.
Note 2: For Requirement 2, acceptable standards for the inspection program are CAO 101.22.3.61 (3) and FAR 23.573.
Compliance: For Requirement 1: Retire before 11000 hours component time in service.
For Requirement 2: Inspect before 11000 hours component time in service, and thereafter at the intervals specified in the approved inspection program.
This Amendment becomes effective on 5 December 1996.
Background: Fatigue analysis predicts the possibility of cracking in the lower wing joint after 11000 hours. Such cracking caused a fatal accident to a similar model with the same style of wing joint.
Amendment 1 re-affirms that all PA-32 series models are subject to the same life limit, even those released after the original issue of this Directive.
Amendment 1 minimises the structure to be retired by limiting it to the components which comprise the lower wing joint. However the Authority has not investigated whether or not it is more practical to replace these components separately instead of replacing the complete wing and carry-through.
Amendment 1 refers to the possibility of inspection as an alternative to retirement.
The original issue of this Airworthiness Directive became effective on 29 October 1976.
Overview
The Civil Aviation Regulations 1998, specifically within Part 39 - 105, address safety directives concerning aircraft airworthiness through the Civil Aviation Safety Authority. The regulations aim to ensure that all aircraft, including the Piper PA-32 (Cherokee Six) series aeroplanes, meet specific safety standards to prevent accidents. Enacted by the Australian Parliament, this legislation seeks to establish a consistent framework for aircraft maintenance and operational safety across the country. The policy objective is to mitigate the risk of structural failure due to fatigue by enforcing specific maintenance directives.
This legislative instrument, Amendment 1, addresses the issue of structural fatigue in the wing main spar assembly and the bottom cap of the wing main spar box in Piper PA-32 series aircraft. The amendment mandates that these components must either be retired from service before reaching 11,000 hours of component time in service or inspected for fatigue cracks in accordance with an approved inspection program. This directive was introduced to prevent potential accidents caused by wing joint failures, as evidenced by a fatal incident involving a similar model. The amendment became effective on 5 December 1996, reaffirming the necessity for rigorous maintenance protocols to ensure the continued safety of these aircraft.
Scope and Application
The Civil Aviation Regulations 1998, under PART 39 - 105, specifically addresses the safety of Piper PA-32 (Cherokee Six) series aeroplanes through an Airworthiness Directive (AD/PA-32/42). This legislative instrument applies to all models within the PA-32 series, mandating strict measures to ensure the integrity of the aircraft's wing structure. The directive is applicable nationally, with the Civil Aviation Safety Authority (CASA) setting forth the requirements to mitigate the risk of wing structural fatigue which has been linked to fatal accidents. The primary requirement is that either the wing main spar assembly and the bottom cap of the wing main spar box (carry through) must be retired from service or an inspection for fatigue cracks must be conducted in accordance with an approved inspection program. The directive mandates compliance by retiring the specified components before they reach 11000 hours of component time in service or conducting inspections at this threshold and then at intervals specified in the approved program. This legislative instrument underscores the importance of stringent safety measures in civil aviation to protect public safety and uphold the highest standards of airworthiness.
Key Provisions
The Civil Aviation Regulations 1998, Part 39, Section 105, outlines a specific Airworthiness Directive (AD) concerning Piper PA-32 (Cherokee Six) series aeroplanes. This directive, AD/PA-32/42 Amendment 1, focuses on addressing wing structural fatigue life limitations (Section 1). The directive applies to all PA-32 series aircraft, encompassing all models (Section 13/96). It mandates two primary actions: either retiring specific components from service or conducting a detailed inspection of the lower wing joint for fatigue cracks according to an approved inspection program (Section 1).
For the retirement requirement, the directive stipulates that the wing main spar assembly and the bottom cap of the wing main spar box (carry-through) must be retired (Section 1.1). Alternatively, an inspection program must be implemented to detect fatigue cracks in the lower wing joint. The inspection must adhere to standards outlined in CAO 101.22.3.61 (3) and FAR 23.573 (Section 2). Compliance with these directives must be achieved before the component time in service reaches 11,000 hours (Section Compliance).
Entities governed by this directive, such as aircraft operators and maintenance organisations, must ensure that either the specified components are retired or that an approved inspection program is carried out before the 11,000-hour limit is reached. This involves meticulous documentation and adherence to the standards set by the Civil Aviation Safety Authority (CASA) to ensure compliance. Failure to comply with these directives can result in severe consequences, including grounding of the aircraft until compliance is achieved, potential fines, and other enforcement actions by CASA.
In terms of penalties, the breach of these directives can lead to significant civil and criminal consequences. The exact penalties are not specified in the directive but can include fines, imprisonment, or both, depending on the severity and frequency of the breach. Such penalties are intended to enforce strict adherence to safety standards and to ensure the continued safety and airworthiness of the PA-32 series aircraft.