AD 97-14-02

This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Industrie Model A300-600 series airplanes, that requires repetitive eddy current inspections to detect cracks of the outer skin of the fuselage at certain frames, and repair or reinforcement of the structure at the frames, if necessary. This amendment also requires eventual reinforcement of the structure at certain frames, which, when accomplished, terminates the repetitive inspections. This amendment is prompted by a report indicating that fatigue cracks were found in the area of certain frames. The actions specified by this AD are intended to prevent such fatigue cracking, which could reduce the structural integrity of the airframe and result in rapid decompression of the airplane.

97-14-02 AIRBUS INDUSTRIE: Amendment 39-10059. Docket 96-NM-182-AD.

Applicability: Model A300-600 series airplanes on which Airbus Modification 8683 was not accomplished during production, or on which Airbus Modification 8684 has not been installed; certificated in any category.

NOTE 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been otherwise 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 fatigue cracking of the fuselage outer skin at frames 28A and 30A, which could reduce the structural integrity of the airframe and result in rapid decompression of the airplane, accomplish the following:

(a) Prior to the accumulation of 14,100 total flight cycles, or within 12 months after the effective date of the AD, whichever occurs later, conduct an eddy current inspection to detect cracking of the fuselage outer skin at frames 28A and 30A above stringer 30, in accordance with Airbus Service Bulletin A300-53-6045, dated March 21, 1995, as revised by Change Notice No. O.A., dated June 1, 1995.

(1) If no cracking is found, repeat the inspection thereafter at intervals not to exceed 4,500 flight cycles.

(2) If any cracking is found that is within the limits specified in the service bulletin, prior to further flight, repair in accordance with paragraph 2.D. of the Accomplishment Instructions of Airbus Service Bulletin A300-53-6045, dated March 21, 1995, as revised by Change Notice No. O.A., dated June 1, 1995; or reinforce the structure at frames 28 and 29, and at frames 30 and 31, between stringers 29 and 30, in accordance with Airbus Service Bulletin A300-53-6037, dated March 21, 1995.

(i) If the repair is accomplished: After the repair, repeat the eddy current inspection thereafter at intervals not to exceed 4,500 flight cycles.

(ii) If the reinforcement is accomplished: Such reinforcement constitutes terminating action for the repetitive inspections required by this AD.

(3) If any cracking is found that is outside the limits specified in the service bulletin, prior to further flight, reinforce the structure at frames 28 and 29, and at frames 30 and 31, between stringers 29 and 30, in accordance with Airbus Service Bulletin A300-53-6037, dated March 21, 1995. Such reinforcement constitutes terminating action for the repetitive inspections required by this AD.

(b) Within 5 years after the effective date of this AD, reinforce the structure at frames 28 and 29, and at frames 30 and 31, between stringers 29 and 30, in accordance with Airbus Service Bulletin A300-53-6037, dated March 21, 1995. Such reinforcement constitutes terminating action for the repetitive inspections required by this AD.

(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, Standardization Branch, ANM-113, 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, Standardization Branch, ANM-113.

NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113.

(d) Specialflight 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) The actions shall be done in accordance with Airbus Service Bulletin A300-53-6045, dated March 21, 1995, as revised by Change Notice No. O.A., dated June 1, 1995; and Airbus Service Bulletin A300-53-6037, dated March 21, 1995. 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.

(f) This amendment becomes effective on August 4, 1997.

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 Industrie Model A300-600 series airplanes was published in the Federal Register on March 26, 1997 (62 FR 14361). That action proposed to require repetitive eddy current inspections to detect cracks of the outer skin of the fuselage at frames 28A and 30A above stringer 30; and repair or reinforcement of the structure of the frames, if necessary. Additionally, that action proposed to require eventual reinforcement of the structure at frames 28 and 29, and frames 30 and 31, between stringers 29 and 30, which, when accomplished, terminates the repetitive inspections.

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.

The FAA has revisedparagraph (a)(2) of this AD by adding the phrase "prior to further flight" to clarify the compliance time for the repair or reinforcement of any cracking found. This phrase was omitted inadvertently from the proposed rule.

The FAA also has removed NOTE 1 of the proposal, which excluded certain airplanes from the applicability of this AD. The FAA considers it unnecessary to include this information in the final rule.

Conclusion
After careful review of the available data, including the changes noted above, the FAA has determined that air safety and the public interest require the adoption of the rule with the changes previously described. The FAA has determined that these changes will neither increase the economic burden on any operator nor increase the scope of the AD.

Cost Impact
The FAA estimates that 34 Airbus Industrie Model A300-600 series airplanes of U.S. registry will be affected by this AD.

The eddy current inspection that is required by this AD will take approximately 1 work hour per airplane to accomplish, at an average labor rate of $60 per work hour. Based on these figures, the cost impact of the required inspection on U.S. operators is estimated to be $2,040, or $60 per airplane, per inspection cycle.

The reinforcement that is required by this AD will take approximately 93 work hours per airplane to accomplish, at an average labor rate of $60 per work hour. Required parts will cost approximately $7,200 per airplane. Based on these figures, the cost impact of the required modification on U.S. operators is estimated to be $434,520, or $12,780 per airplane.

The cost impact figures discussed above are 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 Impact
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 U.S.C. 106(g), 40113, 44701.
39.13 - [Amended]
2. Section 39.13 is amended by adding the following new airworthiness directive: