AD/PA-34/46 Amdt 1 - Main Landing Gear Side Brace Stud

Administered by Department of Infrastructure, Transport, Regional Development, Communications, Sport and the Arts

Legislation au F2006B05916 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/PA-34/46 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-34 (Seneca) Series Aeroplanes

 

AD/PA-34/46

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

PA34-200 all serial numbers

PA34-200T 34-7570001 through 34-7770372

 

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 PA34-200 or PA34-200T 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 PA34-200 and PA34-200T 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 PA-34-200 and PA-34-200T 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.

 

 

 

 

Figure 1

 

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

 

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 seve n 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/PA-34/46 Amendment 1 on 5 September 2002 to address a safety issue concerning the main landing gear side brace studs in Piper PA-34 (Seneca) series aeroplanes. This directive, published under the Civil Aviation Regulations 1998, aims to prevent potential collapse of the main landing gear due to cracks in the side brace studs, which could lead to loss of control during landing operations. The directive revokes the original AD/PA-34/46 and introduces updated requirements and compliance intervals. CASA considers the actions specified in this directive necessary to maintain the airworthiness of affected aircraft and ensure the safety of flight operations. The directive became effective on the date of its publication in the Commonwealth of Australia Gazette on 14 August 2002.

Scope and Application

The Airworthiness Directive (AD) AD/PA-34/46, issued by the Civil Aviation Safety Authority (CASA) under subregulation 39.1 (1) of the Civil Aviation Regulations 1998, applies specifically to Piper PA-34 (Seneca) series aeroplanes, including model numbers PA34-200 and PA34-200T with certain serial numbers, that are not equipped with specified bracket assembly parts. The directive mandates that both left and right main gear side brace studs be removed and inspected for cracks using fluorescent penetrant or magnetic particle inspection methods, as detailed in the aircraft’s maintenance manual. If any stud is found to be cracked, it must be replaced with an approved serviceable part. The directive also specifies that if certain older stud parts are installed, they must either be replaced with a new bracket assembly or the existing bushings must be reamed to specific dimensions before reinstallation. The directive applies to aircraft within the next 100 hours after 4 January 1996 and then at intervals not exceeding 500 hours. This AD is applicable across the Commonwealth of Australia and is enforceable by CASA, which has the authority to extend or restrict its application through subordinate instruments.

Key Provisions

This Airworthiness Directive (AD) issued by the Civil Aviation Safety Authority (CASA) revokes the previous AD AD/PA-34/46 and introduces new requirements concerning the main landing gear side brace studs of certain Piper PA-34 (Seneca) Series aeroplanes. Specifically, the AD applies to the PA34-200 and PA34-200T models that do not have part numbers 95643-06, 95643-07, 95643-08, or 95643-09 bracket assemblies (section 2). The requirement section stipulates that the left and right main gear side brace studs must be removed and inspected for cracks using fluorescent penetrant or magnetic particle inspection methods. If a stud is found cracked, it must be replaced with an approved serviceable part as per the maintenance manual instructions (section 3). Furthermore, if the aircraft is a PA34-200 or PA34-200T model, and the existing bushings can be reamed, they must be reamed to an inside diameter of 0.624 inch to 0.625 inch and chamfered on the head side before reinstalling the stud. If the bushings cannot be reamed while installed, a new bracket assembly must be installed. Repetitive inspections are not required once the specified actions are completed (section 4). The AD imposes obligations on aircraft owners and operators to ensure compliance with the specified actions. Owners and operators must inspect the main landing gear side brace studs within 100 hours of the AD's effective date and then at intervals not exceeding 500 hours of time in service. They must follow the instructions outlined in the maintenance manual and ensure that the required inspections and replacements are carried out properly and timely. Failure to comply with the AD may result in safety risks and potential legal consequences (section 5). Under Australian law, non-compliance with an AD can lead to civil or criminal penalties. Civil penalties for non-compliance may include fines and other enforcement actions by CASA. Criminal penalties may apply if non-compliance results in an aircraft accident or serious incident, with potential fines and imprisonment. The exact penalties depend on the severity of the breach and the circumstances of the non-compliance (section 6).

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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.