AD/PA-32/79 Amdt 1 - Main Landing Gear Side Brace Stud

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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/PA-32/79 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.

 

Piper PA-32 (Cherokee Six) Series Aeroplanes

 

AD/PA-32/79

Amdt 1


Main Landing Gear Side Brace Stud 9/2002

 

Applicability: The following model and serial number aircraft that are not equipped with a part number 95643-06, 95643-07, 95643-08, or 95643-09 bracket assembly, which includes a part number 78717-02 main landing gear side brace stud:

 

Model Serial Numbers

PA32R-300 32R-7680001 through 32R-7780444

Requirement: Remove both the left and right main gear side brace studs from the aircraft in accordance with the instructions contained in the Landing Gear section of the maintenance manual, and inspect each main gear side brace stud for cracks using fluorescent penetrant or magnetic particle inspection methods. Figure 1 of this Directive depicts the area where the sidebrace stud is to be inspected.

This figure is provided to depict the area of the sidebrace stud to be inspected. This is not intended to represent the configuration of all models affected.

Note 1: A part number 95299-00 or 95299-02 stud installed in an applicable Model PA32R-300 aircraft may be identified by removing the stud and measuring the shank diameter of the stud. If the shank measures 5/8 inch in diameter, a part number 78717-02 main gear side brace stud is installed.

 

For any main gear side brace stud found cracked, replace the cracked stud with an approved serviceable part in accordance with the instructions contained in the Landing Gear section of the applicable maintenance manual.

For the affected Model PA32R-300 aircraft, the part number 95299-00 or 95299-02 main gear side brace studs are no longer manufactured. A new main gear side brace stud bracket assembly, part number(s) 95643-06, 95643-07, 95643-08, or 95643-09, as applicable, must be installed if cracks are found as a result of the required inspection. No repetitive inspection will be required for these affected aircraft models when this bracket assembly is installed;

 

or

 

For the affected Model PA32R-300 aircraft, ream the existing two-piece bushings to an inside diameter of 0.624 inch to 0.625 inch, chamfer the head side of the bushing to accommodate the radius in the shank of the main gear side brace stud, and install the 5/8 inch stud, P/N 78717-02. No repetitive inspections will be required by this Airworthiness Directive when this action is accomplished on both the left and right bracket assemblies. If the bushings cannot be reamed while installed in the bracket (i.e., the bushings are loose), then install a main gear side brace bracket assembly, P/N 95643-06, P/N 95643-07, P/N 95643-08, or P/N 95643-09, as applicable.

 

No repetitive inspections will be required by this Airworthiness Directive when a P/N 78717-02 (or CASA approved equivalent part number) main gear side brace stud is installed in the existing bracket assembly on both the left and right sides; or when a bracket assembly, P/N 95643-06 (or CASA approved equivalent part number), P/N 95643-07 (or CASA approved equivalent part number), P/N 95643-08 (or CASA approved equivalent part number), or P/N 95643-09 (or CASA approved equivalent part number), as applicable, is installed on both the left and right sides.

 

Note 2: FAA AD 97-01-01 R1 Amdt 39-10864 refers.

 

 

 

Figure 1

 

Compliance: Within the next 100 hours time in service after 4 January 1996, and thereafter at intervals not to exceed 500 hours time in service.

 

The original compliance times of this Airworthiness Directive are unchanged by this amendment.

 

This amendment becomes effective on 5 September 2002.

 

Background: The FAA received reports of main gear side brace stud cracks, and seven associated incidents where the main landing gear collapsed. The actions specified by this Directive are intended to prevent a main gear collapse caused by main gear side brace stud cracks, which could result in loss of control of the aircraft during landing operations.

Amendment 1 allows reaming of the existing bushings as an alternative to replacing certain bushings.

The original issue of this Airworthiness Directive became effective on 4 January 1996.


David Alan Villiers

Delegate of the Civil Aviation Safety Authority 23 July 2002

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 


The above AD is notified in the Commonwealth of Australia Gazette on 14 August 2002.

Overview

The Civil Aviation Safety Authority (CASA) issued Airworthiness Directive (AD) AD/PA-32/79 Amendment 1 on 23 July 2002, and it was gazetted on 14 August 2002. This AD revokes the earlier AD AD/PA-32/79 and is issued under subregulation 39.1 (1) of the Civil Aviation Regulations 1998. The AD was introduced to address the problem of main gear side brace stud cracks, which had led to several incidents of main landing gear collapse. The policy objective of this AD is to prevent further incidents of main gear collapse by requiring the inspection and replacement of cracked studs or the installation of alternative parts in specific Piper PA-32 (Cherokee Six) Series Aeroplanes, ensuring the continued airworthiness of these aircraft and maintaining safety standards during landing operations.

Scope and Application

The Airworthiness Directive (AD) AD/PA-32/79, as amended, issued under the authority of the Civil Aviation Safety Authority (CASA) applies specifically to Piper PA-32 (Cherokee Six) Series aeroplanes, particularly those in the PA32R-300 model and within certain serial number ranges, which are not equipped with a specified bracket assembly that includes a particular main landing gear side brace stud. This AD mandates the inspection and, if necessary, the replacement of the main gear side brace studs to address identified safety concerns related to potential cracking, which could compromise the structural integrity of the landing gear. The directive applies nationally across the Commonwealth of Australia and requires compliance from aircraft operators, maintenance personnel, and relevant aviation authorities. The AD does not explicitly exclude any specific entities or circumstances from its scope, and compliance is mandatory for the specified aircraft models within the given serial number ranges. The AD’s application may be further detailed or modified through subsequent amendments or subordinate instruments, which may provide additional instructions, clarifications, or changes to the compliance schedule.

Key Provisions

The Airworthiness Directive (AD) AD/PA-32/79 Amendment 1, issued under subregulation 39.1 (1) of the Civil Aviation Regulations 1998, applies specifically to Piper PA-32 (Cherokee Six) Series Aeroplanes, particularly those serial numbers 32R-7680001 through 32R-7780444 that are not equipped with a specific bracket assembly. The directive mandates the removal and inspection of the left and right main gear side brace studs for cracks, and if any are found, they must be replaced with an approved serviceable part. Additionally, the directive allows for the ream of existing bushings as an alternative to replacing them, provided that specific criteria are met. The directive requires these actions to be performed within 100 hours of time in service after 4 January 1996 and then at intervals not exceeding 500 hours of time in service thereafter. The AD imposes specific obligations on the parties involved, including aircraft owners, operators, and maintenance personnel. These obligations include ensuring that the required inspections and maintenance actions are carried out in accordance with the specified instructions and timeframes. Aircraft owners and operators must ensure that the required inspections and repairs are performed by qualified personnel, using the specified methods and approved parts. Maintenance personnel must follow the detailed instructions provided in the Landing Gear section of the applicable maintenance manual, including the use of fluorescent penetrant or magnetic particle inspection methods. Failure to comply with the requirements of the AD may result in serious safety issues, including the potential for main gear collapse during landing operations, which could lead to loss of control of the aircraft. While the AD itself does not explicitly state penalties for non-compliance, failure to adhere to airworthiness directives can result in enforcement actions by the Civil Aviation Safety Authority (CASA), including fines, suspension or revocation of aircraft certificates, and potential criminal charges in cases of gross negligence or willful disregard of safety regulations. These enforcement actions are governed by the Civil Aviation Act 1988 and the Civil Aviation Regulations 1998, which provide for both administrative and criminal penalties for non-compliance with aviation safety regulations.

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Sourced from the Federal Register of Legislation at 26 August 2026. For the latest information on Australian Government law please go to https://www.legislation.gov.au.