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.
Overview
The Civil Aviation Safety Authority (CASA) has issued Airworthiness Directive (AD) AD/CHA/23 Amdt 3, effective from 22 March 2001, to address safety concerns regarding in-flight structural failures of American Champion (Aeronca, Bellanca) Series Aeroplanes, specifically relating to the wooden wing spars. This AD revokes the previous AD/CHA/23 Amdt 2 and introduces more stringent measures for the inspection and maintenance of wing spars to prevent further structural failures. CASA, acting under the authority of the Civil Aviation Regulations 1998, mandates detailed visual inspections of both the front and rear wooden wing spars for cracks, compression cracks, longitudinal cracks, and loose or missing rib nails, using specified inspection methods. The AD applies to two groups of aircraft, with different inspection intervals based on the type and modifications of the aircraft. The directive aims to enhance safety by ensuring that any identified damage is promptly repaired or the affected spars are replaced according to approved practices. This legislative instrument is part of CASA's ongoing efforts to maintain and improve aviation safety standards in Australia.
Scope and Application
The Airworthiness Directive (AD) AD/CHA/23 Amdt 3 issued under the Civil Aviation Regulations 1998 applies specifically to certain American Champion (Aeronca, Bellanca) Series Aeroplanes. This directive targets Group 1 aircraft, which includes 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, provided they have not been modified to incorporate an engine with more than 90 horsepower, and Group 2 aircraft, which includes ACAC Models 7ECA, 7GC, 7GCA, 7GCAA, 7GCB, 7GCBA, 7GCBC, 7HC, 7KC, 7KCAB, 8GCBC, and 8KCAB, as well as any Group 1 aircraft modified to have an engine with more than 90 horsepower. The directive mandates a detailed visual inspection of the wooden wing spars for any signs of damage, such as cracks or loose rib nails, and requires repairs or replacements if any damage is found. The inspections must adhere to the instructions provided in ACAC Service Letter No. 406, Revision A, dated May 6, 1998. This AD extends to all aircraft within the specified groups and is applicable across the Commonwealth of Australia, as notified in the Commonwealth of Australia Gazette on 21 February 2001.
Key Provisions
The main operative sections of this Airworthiness Directive (AD) under subregulation 39.1(1) of the Civil Aviation Regulations 1998 (CAR 1998) (section 1) are the applicability and requirement sections. The applicability section identifies the specific American Champion (Aeronca, Bellanca) Series Aeroplanes subject to the AD, which includes Group 1 aircraft such as 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, and Group 2 aircraft such as 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 (section 2). The requirement section sets out the mandatory actions to be taken, including performing a detailed visual inspection of the front and rear wood wing spars for cracks, compression cracks, longitudinal cracks, and loose or missing rib nails (section 3).
The AD imposes several obligations and requirements on the parties or entities it governs. Firstly, the AD requires a detailed visual inspection of the entire length of the front and rear wood wing spars of the specified aircraft. This inspection must be carried out in accordance with the instructions provided in ACAC Service Letter No. 406, Revision A, dated May 6, 1998, and must not be conducted using a regular flashlight (section 3(1)). Secondly, if any aircraft is involved in an accident or incident that involves wing damage, the inspection specified in Requirement 1 must be accomplished (section 3(2)). Thirdly, if any damage is found during any inspection, the wood spar must be repaired or replaced 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 (section 3(3)).
Failure to comply with the AD can result in civil and criminal consequences. The AD does not explicitly outline specific offences or penalties, but non-compliance with ADs generally can lead to enforcement actions by the Civil Aviation Safety Authority (CASA). Such actions may include fines, suspension or revocation of airworthiness certificates, and potential criminal charges for wilful non-compliance. The maximum penalties for offences under the CAR 1998 can include fines of up to $210,000 for individuals and $1,050,000 for corporations, as well as imprisonment terms of up to five years for individuals and seven years for corporations. Additionally, non-compliance can result in the grounding of aircraft, which can have significant financial implications for operators and can also impact public safety.