- Effective
- May 16, 2000
- Published
- April 11, 2000 · 65 FR 19308–19310
- Issued
- March 31, 2000
- Models
- A300 B2-1A, A300 B2-1C, A300 B2-203, A300 B2K-3C, A300 B4-103, A300 B4-203, A300 B4-2C
- Product
- Aircraft · Large airplane
- Amendment
- 39-11661
- Docket
- 99-NM-205-AD
- Issued as
- Final rule
Unofficial copy from the Federal Register XML, document 00-8514. Only the govinfo PDF is the legal edition. DRS record last changed May 30, 2024.
Copies of the files this page was built from, with their SHA-256. Retrieved October 18, 2026.
| File | Size | SHA-256 | Original |
|---|---|---|---|
| Official PDF | 225 KB | 00600086…222a888 | 00-8514.pdf on govinfo.gov |
| Federal Register XML | 15 KB | 533fc55a…0769bac | 00-8514.xml on federalregister.gov |
| FAA DRS HTML | 47 KB | e9061145…4bcf28d | FAA DRS (API key needed) |
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Summary
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300 series airplanes, that requires modification of wing center box angle fittings at frame 47. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent reduced structural integrity of the wing center box angle fittings at frame 47 due to fatigue cracking.
The airworthiness directive
2000-07-07 Airbus Industrie: Amendment 39-11661. Docket 99-NM-205-AD.
Applicability: Model A300 series airplanes, as listed in Airbus Service Bulletin A300-53-0298, Revision 03, dated November 26, 1998; certificated in any category; except those on which Airbus Service Bulletin A300-53-0282 or Airbus Service Bulletin A300-53-0291 has been accomplished.
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 request approval for an alternative method of compliance in accordance with paragraph (c) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it.
Compliance: Required as indicated, unless accomplished previously.
To prevent reduced structural integrity of the wing center box angle fittings at frame (FR) 47, accomplish the following:
(a) Prior to the accumulation of the applicable threshold specified in the “MANDATORY TH” column of the table in paragraph 1.B.(4) of the service bulletin, or within 6,500 flight cycles after the effective date of this AD, whichever occurs later: Except as required by paragraph (b) of this AD, modify the wing center box angle fittings at FR 47 (including removing certain sealant and fasteners, performing rotating probe inspections to detect cracking, cold working certain fastener holes, installing new fasteners and sealant, and repairing damage), in accordance with Airbus Service Bulletin A300-53-0298, Revision 03, dated November 26, 1998.
Note 2:
Operators should note that the area required to be modified by paragraph (a) of this AD remains subject to the requirements of AD 96-13-11, amendment 39-9679, after modification.
(b) Where Airbus Service Bulletin A300-53-0298, Revision 03, dated November 26, 1998, specifies that Airbus be contacted for repair instructions for certain damage conditions, this AD requires that such damage conditions be repaired prior to further flight in accordance with a method approved by either the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate; or the Direction Ge ne rale de l'Aviation Civile (DGAC) (or its delegated agent). For a repair method to be approved by the Manager, International Branch, ANM-116, as required by this paragraph, the Manager's approval letter must specifically reference this AD.
(c) Alternative Methods of Compliance
PDF page 2(c) 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, International Branch, ANM-116, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, International Branch, ANM-116.
Note 3:
Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the International Branch, ANM-116.
(d) Special Flight Permits
PDF page 2(d) 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.
(e) Incorporation by Reference
PDF page 2(e) Except as provided by paragraph (b) of this AD, the modification shall be done in accordance with Airbus Service Bulletin A300-53-0298, Revision 03, dated November 26, 1998, which contains the following list of effective pages:
| Page number | Revision level shown on page | Date shown on page |
|---|---|---|
| 1-21, 32-40, 42-46, 67, 68, 71-74, 93, 94, 103-110, 151, 157-161, 205-214 | 03 | November 26, 1998. |
| 22-31, 41, 47-55, 57-66, 69, 70, 75-92, 95-102, 152-156, 163-204, 215 | Original | October 14, 1993. |
| 56, 102A, 102B, 111-150 | 1 | March 17, 1994. |
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.
Note 4:
The subject of this AD is addressed in French airworthiness directive 1999-076-267(B), dated February 24, 1999.
(f) This amendment becomes effective on May 16, 2000.
Rule preamble
The FAA’s background, reasoning and cost estimate, published with the AD.
DatesPage 1
Effective May 16, 2000.
The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of May 16, 2000.
AddressesPage 1
The service information referenced in this AD may be obtained from Airbus Industrie, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. This information may be examined at the Federal Aviation Administration (FAA), Transport Airplane Directorate, Rules Docket, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC.
For further information contactPage 1
Norman B. Martenson, Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 227-2110; fax (425) 227-1149.
Supplementary informationPage 1
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 certain Airbus Model A300 series airplanes was published in the Federal Register on January 27, 2000 (65 FR 4386). That action proposed to require modification of wing center box angle fittings at frame 47.
CommentsPage 2
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 states that it is not affected by the proposal.
ConclusionPage 2
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.
Cost impactPage 2
The FAA estimates that 38 airplanes of U.S. registry will be affected by this AD, that it will take approximately 430 work hours per airplane to accomplish the required modification, and that the average labor rate is $60 per work hour. Required parts will cost approximately $8,840 per airplane. Based on these figures, the cost impact of the AD on U.S. operators is estimated to be $1,316,320, or $34,640 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.
Regulatory impactPage 2
The regulations adopted herein will not have a substantial direct effect 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, it is determined that this final rule does not have federalism implications under Executive Order 13132.
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.
Adoption of the amendmentPage 2
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:
1. The authority citation for part 39 continues to read as follows:
2. Section 39.13 is amended by adding the following new airworthiness directive: