- Effective
- December 27, 1995
- Published
- November 27, 1995 · 60 FR 58213–58215
- Superseded by
- AD2015-02-19
- Models
- A300 B2-1A, A300 B2-1C, A300 B2-203, A300 B2K-3C, A300 B4-103, A300 B4-203 and 8 more
- Data sheet
- TCDSA35EU
- Registered aircraft
- 118 matched by model
- Product
- Aircraft · Large airplane
- Amendment
- 39-9436
- Docket
- 95-NM-04-AD
- Issued as
- Final rule
Unofficial copy of the text in the FAA’s Dynamic Regulatory System. Only the govinfo PDF is the legal edition. DRS record last changed August 7, 2025.
Copies of the files this page was built from, with their SHA-256. Retrieved October 18, 2026.
| File | Size | SHA-256 | Original |
|---|---|---|---|
| Official PDF | 126 KB | 8c922b16…0c77c32 | 95-28798.pdf on govinfo.gov |
| FAA DRS HTML | 46 KB | b53fea55…c6792c5 | FAA DRS (API key needed) |
| Federal Register text | 11 KB | 4e37ae48…b4a0e97 | 95-28798.txt on federalregister.gov |
On this page
Summary
This amendment adopts a new airworthiness directive (AD), applicable to all Airbus Model A300 and A300-600 series airplanes, that requires repetitive eddy current inspections to detect cracks at the aft spar web of the wings, and repair, if necessary. This amendment is prompted by reports indicating that cracks have been found in the rear spar web of the wings between ribs 1 and 2 of an in-service airplane and during testing on the fatigue test wing; the cracking occurred due to fatigue-related high shear stress. The actions specified by this AD are intended to prevent such fatigue-related cracking, which could result in reduced structural integrity of the wing.
The airworthiness directive
95-24-04 AIRBUS INDUSTRIE: Amendment 39-9436. Docket 95-NM-04-AD.
Applicability: All Model A300 and Model A300-600 series airplanes, certificated in any category.
NOTE 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must use the authority provided in paragraph (f) of this AD to request approval from the FAA. This approval may address either no action, if the current configuration eliminates the unsafe condition; or different actions necessary to address the unsafe condition described in this AD. Such a request should include an assessment of the effect of the changed configuration on the unsafe condition addressed by this AD. In no case does the presence of any modification, alteration, or repair remove any airplane from the applicability of this AD.
Compliance: Required as indicated, unless accomplished previously.
To prevent fatigue-related cracking in the rear spar web of the wings, which could result in reduced structural integrity of the wing, accomplish the following:
(a) For Model A300 B2 series airplanes: Prior to the accumulation of 18,000 total flight cycles or within 1,400 flight cycles after the effective date of this AD, whichever occurs later, perform a high frequency eddy current (HFEC) inspection to detect cracks at the aft spar web of the wings, in accordance with Airbus Service Bulletin A300-57-0213, dated August 12, 1994. Repeat the inspection thereafter at intervals not to exceed 5,000 flight cycles.
(b) For Model A300 B4-103, and B4-2C series airplanes: Prior to the accumulation of 19,000 total flight cycles or within 1,400 flight cycles after the effective date of this AD, whichever occurs later, perform an HFEC inspection to detect cracks at the aft spar web of the wings, in accordance with Airbus Service Bulletin A300-57-0213, dated August 12, 1994. Repeat the inspection thereafter at intervals not to exceed 6,000 flight cycles.
(c) For Model A300 B4-200 series airplanes: Prior to the accumulation of 17,000 total flight cycles or within 1,400 flight cycles after the effective date of this AD, whichever occurs later, perform an HFEC inspection to detect cracks at the aft spar web of the wings, in accordance with Airbus Service Bulletin A300-57-0213, dated August 12, 1994. Repeat the inspection thereafter at intervals not to exceed 5,000 flight cycles.
(d) For Model A300-600 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R, and F4-605R series airplanes: Prior to the accumulation of 21,600 flight cycles, perform an HFEC inspection to detect cracks at the aft spar web of the wings, in accordance with Airbus Service Bulletin A300-57-6059, dated August 12, 1994. Repeat the inspection thereafter at intervals not to exceed 5,700 flight cycles.
(e) If any crack is detected during any inspection required by this AD, prior to further flight, repair the crack in accordance with Airbus Service Bulletin A300-57-0213, dated August 12, 1994, or Airbus Service Bulletin A300-57-6059, dated August 12, 1994, as applicable; or in accordance with a method approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate.
(f) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Standardization Branch, ANM-113. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Standardization Branch, ANM-113.
NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained fromthe Standardization Branch, ANM-113.
(g) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished.
(h) The inspections and repair shall be done in accordance with Airbus Service Bulletin A300-57-0213, dated August 12, 1994, or Airbus Service Bulletin A300-57-6059, dated August 12, 1994, as applicable. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from Airbus Industrie, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC.
(i) This amendment becomes effective on December 27, 1995.
Rule preamble
The FAA’s background, reasoning and cost estimate, published with the AD.
Supplementary information
A proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to include an airworthiness directive (AD) that is applicable to all Airbus Model A300 and A300-600 series airplanes was published in the Federal Register on May 4, 1995 (60 FR 22011). That action proposed to require repetitive eddy current inspections to detect cracks at the aft spar web of the wings, and repair, if necessary.
Interested persons have been afforded an opportunity to participate in the making of this amendment. Due consideration has been given to the single comment received.
The commenter supports the proposed rule.
After careful review of the available data, including the comment noted above, the FAA has determined that air safety and the public interest require the adoption of the rule as proposed.
The FAA estimates that 89 airplanes of U.S. registry will be affected by this AD, that it will take approximately 3 work hours per airplane to accomplish the required actions, and that the average labor rate is $60 per work hour. Based on these figures, the cost impact of the AD on U.S. operators is estimated to be $16,020, or $180 per airplane.
The cost impact figure discussed above is based on assumptions that no operator has yet accomplished any of the requirements of this AD action, and that no operator would accomplish those actions in the future if this AD were not adopted.
The regulations adopted herein will not have substantial direct effects on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. Therefore, in accordance with Executive Order 12612, it is determined that this final rule does not have sufficient federalism implications to warrant the preparation of a Federalism Assessment.
For the reasons discussed above, I certify that this action (1) is not a "significant regulatory action" under Executive Order 12866; (2) is not a "significant rule" under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and (3) will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. A final evaluation has been prepared for this action and it is contained in the Rules Docket. A copy of it may be obtained from the Rules Docket at the location provided under the caption "ADDRESSES."
List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety.
Adoption of the Amendment Accordingly, pursuant to the authority delegated to me by the Administrator, the Federal Aviation Administration amends part 39 of the Federal Aviation Regulations (14 CFR part 39) as follows:
PART 39 - AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: Authority: 49 USC 106(g), 40101, 40113, 44701. 39.13 - [Amended]
Affected TCDS · 1
The type certificate data sheets for the models this AD names, matched by model and maker.
Registered aircraft · 118
Registered aircraft whose airframe or engine model this AD names. Matched by model only, so check each against the AD’s applicability.
| 1988 | 1 |
|---|---|
| 1989 | 2 |
| 1990 | 5 |
| 1991 | 3 |
| 1992 | 7 |
| 1993 | 5 |
| 1994 | 5 |
| 1995 | 8 |
| 1996 | 5 |
| 1997 | 5 |
| 1998 | 6 |
| 1999 | 6 |
| 2000 | 7 |
| 2001 | 11 |
| 2002 | 6 |
| 2003 | 8 |
| 2004 | 7 |
| 2005 | 7 |
| 2006 | 6 |
| 2007 | 6 |
2 with no year recorded