Airworthiness Directives; Airbus Model A300 and A300-600 Series Airplanes

AGENCY:

Federal Aviation Administration, DOT.

ACTION:

Notice of proposed rulemaking (NPRM).

SUMMARY:

This document proposes the adoption of a new airworthiness directive (AD) that is applicable to certain Airbus Model A300 series airplanes and all Airbus Model A300-600 series airplanes. This proposal would require a one-time high frequency eddy current inspection to detect cracking of the splice fitting at fuselage frame (FR) 47 between stringers 24 and 25, and corrective actions, if necessary. This proposal is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by the proposed AD are intended to detect and correct cracking of the splice fitting at fuselage FR47, which could result in reduced structural integrity of the airplane.

DATES:

Comments must be received by May 5, 2000.

ADDRESSES:

Submit comments in triplicate to the Federal Aviation Administration (FAA), Transport Airplane Directorate, ANM-114, Attention: Rules Docket No. 2000-NM-47-AD, 1601 Lind Avenue, SW., Renton, Washington 98055-4056. Comments may be inspected at this location between 9:00 a.m. and 3:00 p.m., Monday through Friday, except Federal holidays.

The service information referenced in the proposed rule may be obtained from Airbus Industrie, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. This information may be examined at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington.

FOR FURTHER INFORMATION CONTACT:

Norman B. Martenson, Manager, International Branch, ANM-116, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 227-2110; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION:

Comments Invited

Interested persons are invited to participate in the making of the proposed rule by submitting such written data, views, or arguments as they may desire. Communications shall identify the Rules Docket number and be submitted in triplicate to the address specified above. All communications received on or before the closing date for comments, specified above, will be considered before taking action on the proposed rule. The proposals contained in this notice may be changed in light of the comments received.

Comments are specifically invited on the overall regulatory, economic, environmental, and energy aspects of the proposed rule. All comments submitted will be available, both before and after the closing date for comments, in the Rules Docket for examination by interested persons. A report summarizing each FAA-public contact concerned with the substance of this proposal will be filed in the Rules Docket.

Commenters wishing the FAA to acknowledge receipt of their comments submitted in response to this notice must submit a self-addressed, stamped postcard on which the following statement is made: “Comments to Docket Number 2000-NM-47-AD.” The postcard will be date stamped and returned to the commenter.

Availability of NPRMs

Any person may obtain a copy of this NPRM by submitting a request to the FAA, Transport Airplane Directorate, ANM-114, Attention: Rules Docket No. 2000-NM-47-AD, 1601 Lind Avenue, SW., Renton, Washington 98055-4056.

Discussion

The Direction Generale de l'Aviation Civile (DGAC), which is the airworthiness authority for France, notified the FAA that an unsafe condition may exist on certain Airbus Model A300 series airplanes and all Airbus Model A300-600 series airplanes. The DGAC advises that it has received reports indicating that cracking occurred in the area surrounding the fastener holes that attach the splice fitting to fuselage frame (FR) 47 on airplanes on which Airbus Modification 5890 had been installed. This modification specifies cold working of the fastener holes in the splice fitting at fuselage FR47. As a result of a laboratory analysis of the cracked splice fittings, the DGAC further advises that inspection of all subject airplanes to detect cracking of the splice fitting at fuselage FR47 is necessary, regardless of whether the modification is installed. Such cracking, if not detected and corrected, could result in reduced structural integrity of the airplane.

Explanation of Relevant Service Information

The manufacturer has issued Airbus All Operators Telexes (AOT) A300-53A0350 (for Model A300 series airplanes) and A300-600-53A6123 (for Model A300-600 series airplanes), both dated October 25, 1999. These AOT's describe procedures for a one-time high frequency eddy current (HFEC) inspection to detect cracking of the splice fitting at fuselage FR47 between stringers 24 and 25, and corrective actions, if necessary. The corrective actions involve additional HFEC inspections to determine whether any cracking extends beyond fastener “A” of the splice fitting at fuselage FR47 and to detect cracking in the area surrounding the fastener holes of the splice fitting on the face of FR47. If cracking is determined to extend beyond fastener ‘A’, but is not detected in the area surrounding the fastener holes, the corrective actions involve replacing the splice fitting with a new splice fitting. The DGAC classified these AOT's as mandatory and issued French airworthiness directive 1999-515-298(B), dated December 29, 1999, in order to assure the continued airworthiness of these airplanes in France.

FAA's Conclusions

These airplane models are manufactured in France and are type certificated for operation in the United States under the provisions of § 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and the applicable bilateral airworthiness agreement. Pursuant to this bilateral airworthiness agreement, the DGAC has kept the FAA informed of the situation described above. The FAA has examined the findings of the DGAC, reviewed all available information, and determined that AD action is necessary for products of this type design that are certificated for operation in the United States.

Explanation of Requirements of Proposed Rule

Since an unsafe condition has been identified that is likely to exist or develop on other airplanes of the same type design registered in the United States, the proposed AD would require a one-time high frequency eddy current inspection to detect cracking of the splice fitting at fuselage FR47 between stringers 24 and 25, and corrective actions, if necessary. The actions would be required to be accomplished in accordance with the AOT's described previously, except as discussed below.

Differences Between Proposed AD and Related Service Information

Operators should note that, although the Airbus AOT's specify that the manufacturer may be contacted for disposition of certain conditions, this proposal would require the repair of those conditions to be accomplished in accordance with a method approved by either the FAA or the DGAC (or its delegated agent). In light of the type of repair that would be required to address the identified unsafe condition, and in consonance with existing bilateral airworthiness agreements, the FAA has determined that, for the proposed AD, a repair approved by either the FAA or the DGAC would be acceptable for compliance with this proposed AD.

The Airbus AOT's describe procedures for an additional HFEC inspection, which under certain circumstances allows operators to defer replacement of the splice fitting. This proposed AD would not require this inspection. Unlike the procedures described in the Airbus AOT's, this proposed AD would not permit further flight if cracks are detected in the splice fitting at fuselage FR47. The FAA has determined that, because of the safety implications and consequences associated with such cracking, any subject area that is found to be cracked must be repaired or modified prior to further flight.

Interim Action

This is considered to be interim action until final action is identified, at which time the FAA may consider further rulemaking.

Cost Impact

The FAA estimates that 83 airplanes of U.S. registry would be affected by this proposed AD, that it would take approximately 1 work hour per airplane to accomplish the proposed one-time HFEC inspection, and that the average labor rate is $60 per work hour. Based on these figures, the cost impact of the proposed AD on U.S. operators is estimated to be $4,980, or $60 per airplane.

The cost impact figure discussed above is based on assumptions that no operator has yet accomplished any of the proposed 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 proposed herein would 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 proposal would not have federalism implications under Executive Order 13132.

For the reasons discussed above, I certify that this proposed regulation (1) is not a “significant regulatory action” under Executive Order 12866; (2) is not a “significant rule” under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and (3) if promulgated, 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 copy of the draft regulatory evaluation prepared for this action is contained in the Rules Docket. A copy of it may be obtained by contacting the Rules Docket at the location provided under the caption ADDRESSES.

List of Subjects 14 CFR Part 39

• Air transportation
• Aircraft
• Aviation safety
• Safety

The Proposed Amendment

Accordingly, pursuant to the authority delegated to me by the Administrator, the Federal Aviation Administration proposes to amend 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.