AIRWORTHINESS DIRECTIVE For the reasons set out in the background section, the CASA delegate whose signature appears below revokes Airworthiness Directive (AD) AD/CHA/23 Amdt 2 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. American Champion (Aeronca, Bellanca) Series Aeroplanes AD/CHA/23 Amdt 3 Wing Spars 3/2001 Applicability: Group 1 aircraft: ACAC Models 7AC, 7ACA, S7AC, 7BCM (L-16A), 7CCM (L- 16B), S7CCM, 7DC, S7DC, 7EC, S7EC, 7FC, 7JC, 11AC, S11AC, 11BC, S11BC, 11CC, and S11CC aircraft that have not been modified to incorporate an engine with greater than 90 horsepower. Group 2 aircraft: ACAC Models 7ECA, 7GC, 7GCA, 7GCAA, 7GCB, 7GCBA, 7GCBC, 7HC, 7KC, 7KCAB, 8GCBC, and 8KCAB aircraft; and any of the Group 1 aircraft that have been modified to incorporate an engine with greater than 90 horsepower. Requirement: 1. Perform a detailed visual inspection of the entire length of the front and rear wood wing spars for cracks, compression cracks, longitudinal cracks through the boltholes or nail holes, or loose or missing rib nails. Accomplish in accordance with the instructions in ACAC Service Letter No. 406, Revision A, dated May 6, 1998. This service letter specifies, as an FAA-approved inspection option, using a high-intensity flexible light (e.g., "Bend-A-Light"). A regular flashlight must not be used for this portion of the inspection. 2. If, after 22 March 2001 any aircraft is involved in an accident/incident that involves wing damage (e.g., wing surface deformations such as abrasions, gouges, scratches, or dents, etc.), accomplish the inspection specified in Requirement 1. 3. If any damage is found during any inspection required by this Directive, repair or replace the wood spar, in accordance with Advisory Circular 43.13-1B, Acceptable Methods, Techniques, and Practices; or other data that is FAA-approved for wing spar repair or replacement. Note : FAA AD 2000-25-02 Amdt 39-12036 refers. Compliance: 1. For Group 1 aircraft: Initially inspect at the first annual inspection that occurs 30 calendar days or more after 22 March 2001 or within the next 13 calendar months after 22 March 2001, whichever occurs later American Champion (Aeronca, Bellanca) Series Aeroplanes AD/CHA/23 Amdt 3 (Continued) For Group 2 aircraft: Initially inspect at the first annual inspection that occurs 30 calendar days or more after 22 March 2001 or within the next 13 calendar months after 22 March 2001, whichever occurs later. Repetitively inspect thereafter at intervals not to exceed 500 hours time in service or 12 calendar months, whichever occurs first. 2. Before further flight after each accident/incident that involved wing damage. 3. Before further flight after the inspection where the damage is found. This amendment becomes effective on 22 March 2001. Background: Accidents caused by in-flight structural failure of the wings were attributed to compression failures in the wooden wing spars. Significant compression failures have also been found in other areas not addressed by FAA AD 87-18-09. Amendment 2 required repetitive inspections of the front and rear spars for damage, including installing any necessary inspection holes, and repairing or replacing any damaged spar. The FAA actions resulted from in-flight wing structural failure on one of the affected aircraft that was in compliance with AD 87-18-09, plus four other ACAC Model 8GCBC accidents and eleven service difficulty reports of compression cracked spars. Amendment 3 is issued in response to a new FAA AD which retains the actions of AD 98-05-04 for the Model 8GCBC aircraft; extends the actions to all 7,8, and 11 series aircraft, and incorporates alternative methods of accomplishing the actions. The AD is the result of a review of the service history of the affected aircraft that incorporate wood wing spars and of damage found on the spars. Amendment 2 of this Airworthiness Directive became effective on 12 August 1999. Amendment 1 of this Airworthiness Directive became effective on 16 May 1991. The original issue of this Airworthiness Directive became effective on 3 December 1987. David Alan Villiers Delegate of the Civil Aviation Safety Authority 9 February 2001 The above AD is notified in the Commonwealth of Australia Gazette on 21 February 2001.