1AD/CHA/23 Amdt 4 - Wing Spars

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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/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.

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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