Airworthiness Directive · Amendment 39-12036 · American Champion Aircraft Corporation 7, 8, and 11 Series Airplanes
American Champion Aircraft Corporation 7, 8, and 11 Series Airplanes
Superseded. A later AD replaced this one: AD 2000-25-02 R1. Comply with the one in force.
This AD applies to the following airplane models, all serial numbers, certificated in any category, that are equipped with wood wing spars:
(1) Group 1 airplanes: 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 airplanes that have not been modified to incorporate an engine with greater than 90 horsepower.
(2) Group 2 airplanes: ACAC Models 7ECA, 7GC, 7GCA, 7GCAA, 7GCB, 7GCBA, 7GCBC, 7HC, 7KC, 7KCAB, 8GCBC, and 8KCAB airplanes; and any of the airplane models referenced in paragraph (a)(1) of this AD that have been modified to incorporate an engine with greater than 90 horsepower.
This amendment supersedes Airworthiness Directive (AD) 98-05- 04, which currently requires you to repetitively inspect the front and rear wood spars for damage (including installing any as-needed inspection holes) and repair or replace any damaged wood spar on certain American Champion Aircraft Corporation (ACAC) Model 8GCBC airplanes. Damage is defined as cracks, compression cracks, longitudinal cracks through the bolt holes or nail holes, or loose or missing nails. This AD retains the actions of AD 98-05-04 for the ACAC Model 8GCBC airplanes; extends the actions to all ACAC 7, 8, and 11 series airplanes (except the inspections are not repetitive for certain 7 and 11 series airplanes); incorporates alternative methods of accomplishing the actions; and requires reporting any damage found. This AD is the result of a review of the service history of the affected airplanes that incorporate wood wing spars where damage was found in this area and consideration of all public comments received. The actions specified by this AD are intended to detect and repair or replace damaged wood wing spars. Continued operation with such damage could progress to in-flight structural failure of the wing with consequent loss of control of the airplane.
For any Group 1 airplane as referenced in paragraph (a)(1) of this AD, the following must be accomplished to address the problem:
| Action | Compliance time | Procedures |
|---|---|---|
| (1) Inspection Requirements: Inspect (detailed visual) 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. We will refer to these conditions as damage throughout the rest of this section | Initially inspect at the first annual inspection that occurs 30 calendar days or more after January 19, 2001 (the effective date of this AD), whichever occurs later | Accomplish in accordance with the instructions in ACAC Service Letter No. 406, Revision A, dated May 6, 1998. This service bulletin 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. Alternative FAA-approved inspection options are listed in this service bulletin. |
| (2) Additional Inspection Requirements: If, after January 19, 2001 (the effective day of this AD), any airplane 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 required in paragraph (d)(1) of this Ad | Prior to further flight after each accident/incident that involved wing damage | Accomplish in accordance with the instructions in ACAC Service Letter No. 406, Revision A, dated May 6, 1998. This service bulletin 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. Alternative FAA-approved inspection options are listed in this service bulletin. |
| (3) Replacement Requirements: If any damage is found during any inspection required by this AD, repair or replace the wood spar | Prior to further flight after the inspection where the damage is found | In accordance with Advisory Circular (AC) 43.13-1B, Acceptable Methods, Techniques, and Practices; or other data that is FAA-approved for wing spar repair or replacement. |
| (4) Reporting Requirements: If any damage is found during any inspection required by this AD, submit a Malfunction or Defect Report (M or D), FAA Form 8010-4, to the FAA | Within 10 days after the inspection where the damage was found or within 10 days after January 19, 2001 (the effective date of this AD), whichever occurs later | Mail the information to: FAA, Chicago Aircraft Certification Office (ACO), Attention: Docket No. 98-CE-121-AD, 2300 E. Devon avenue, Des Plaines, Illinois 60018; facsimile: (847) 294-7834. You may also file electronically as discussed in this AD. |
| (i) Include the airplane model and serial number, the extent of the damage (location and type), and the number of total hours time-in-service (TIS) on the damaged wing | ||
| (ii) You may submit M or D reports electronically by accessing the FAA AFS-600 web page at http://www.mmac.jccbi.gov/afs/afs600. Because you will lose access to the report once you electronically submit it, we recommend that you print two copies prior to submitting the report and forward one to the Chicago ACO and keep the other for your records | ||
| (iii) The Office of Management and Budget (OMB) approved the information collection requirements contained in this regulation under the provisions of the Paperwork Reduction Act of 1980 (14 U.S.C. 3501 et seq.). The OMB assigned this approval Control Number 2120-0056 |
For any Group 2 airplane as referenced in paragraph (a)(2) of this AD, the following must be accomplished to address the problem:
| Action | Compliance time | Procedures |
|---|---|---|
| (1) Inspection Requirements: Inspect (detailed visual) 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. We will refer to these conditions as damage throughout the rest of this section | Initially inspect at the first annual inspection that occurs 30 calendar days or more after January 19, 2001 (the effective dae of this AD) or within the next 13 calendar months after January 19, 2001 (the effective date of this AD), whichever occurs later. Repetitively inspect thereafter at intervals not to exceed 500 hours time-in-service (TIS) or 12 calendar months, whichever occurs first | Accomplish in accordance with the instructions in American Champion Aircraft Corporation (ACAC) Service Letter No. 406, Revision A, dated May 6, 1998. This service bulleting specifies 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. Alternative FAA-approved inspection options are listed in this service bulletin. |
| (2) Additional Inspection Requirements: If, after January 19, 2001 (the effective date of this AD), any airplane 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 required in paragraph (e)(1) of this AD | Prior to further flight after each accident/incident that involved wing damage | Accomplish in accordance with the instuctions in American Champion Aircraft Corporation (ACAC) Service Letter No. 406, Revision A, dated May 6, 1998. This service bulletin specifies 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. Alternative FAA-approved inspection options are listed in this service bulletin. |
| (3) Replacement Requirements: If any damage is found during any inspection required by this AD, repair or replace the wood spar | Prior to further flight after the inspection where the damage is found | In accordance with Advisory Circular (AC) 43.13-1B, Acceptable Methods, Techniques, and Practices; or other data that is FAA-approved for wing spar repair or replacement. |
| (4) Reporting Requirement: If any damage is found during any inspection required by this AD, submit a Malfunction or Defect Report (M or D), FAA Form 8010-4, to the FAA | Within 10 days after the inspection where the damage was found or within 10 days after January 19, 2001 (the effective date of this AD), whichever occurs later | Mail the information to: FAA, Chicago Aircraft Certification Office (ACO), Attention: Docket No. 98-CE-121-AD, 2300 E. Devon Avenue, Des Plaines, Illinois 60018; facsimile: (847) 294-7834. You may also file electronically as discussed in this AD. |
| (i) Include the airplane model and serial number, the extent of the damage (location and type), and the number of total TIS on the damaged wing | ||
| (ii) You may submit M or D reports electronically by accessing the FAA AFS-600 web page at http://www.mmac.jccbi.gov/afs/afs600. Because you will lose access to the report once you electronically submit it, we recommend printing two copies prior to submitting the report and forward one to the Chicago ACO and keep the other for your records | ||
| (iii) The Office of Management and Budget (OMB) approved the information collection requirements contained in this regulation under the provisions of the Paperwork Reduction Act of 1980 (14 U.S.C. 3501 et seq.). The OMB assigned this approval Control Number 2120-0056 |
The aircraft, engines and makers this AD names, by the model designations in its text. A model listed here may still be outside the AD's serial ranges.
Aircraft
