AIRWORTHINESS DIRECTIVE For the reasons set out in the background section, the CASA delegate whose signature appears below revokes Airworthiness Directive (AD) AD/PA-28/91 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-28 Series Aeroplanes AD/PA-28/91 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 PA28R-180 28R-30002 through 28R-31135, and 28R-7130001 through 28R-7130013 PA28R-200 28R-35001 through 28R-35820, and 28R-7135001 through 28R-7635539 PA28R-201 28R-7737002 through 28R-7737096 PA28R-201T 28R-7703001 through 28R-7703239 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 PA28R-180, -200, -201, or -201T 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. Piper PA-28 Series Aeroplanes AD/PA-28/91 Amdt 1 (continued) For the affected Models PA28R-180, -200, -201, and -201T 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-28R-180, PA-28R-200, PA-28R-201, and PA-28R-201T 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. Models PA-28R-180 with serial numbers 28R-30004 through 28R-31270 and PA-28R-200 with serial numbers 28R-35001 through 28R-35820 and 28R-7135001 through 28R-7135062, may be equipped with a bracket casting identified with casting number 67073-2 or 67073-3 and may require the following modification to P/N 78717-02 for proper installation: 1. Reduce the length of the stud to 1.688  0.15 inches; 2. Add additional rolled threads to 1.125  0.015 inches from the flange. Note that the stud is heat treated to 180 to 200 ksi; and c. Drill an additional roll pin hole 90 degrees to the existing hole, and approximately 1.480 inches from the flange. 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. Piper PA-28 Series Aeroplanes AD/PA-28/91 Amdt 1 (continued) 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. Piper PA-28 Series Aeroplanes AD/PA-28/91 Amdt 1 (continued) 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.