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Proposed Rule

Airworthiness Directives; Airbus Model A310 Series Airplanes

Document Details

Information about this document as published in the Federal Register.

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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 A310 series airplanes. This proposal would require modification of the position 1 flap screw jack. 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 prevent fracture of the lead screw of the position 1 flap screw jack, which could result in failure of the tie bar and possible disconnection of the flap structure from the airplane.

DATES:

Comments must be received by May 19, 2000.

ADDRESSES:

Submit comments in triplicate to the Federal Aviation Administration (FAA), Transport Airplane Directorate, ANM-114, Attention: Rules Docket No. 2000-NM-77-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.

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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

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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-77-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-77-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 A310 series airplanes. The DGAC advises that, during routine maintenance, a fractured lead screw was detected in a position 1 flap screw jack. After an inspection of the fleet, additional occurrences of broken or cracked lead screws were reported. Investigation into the fractured lead screws revealed that the cause was attributed to interference between the ball nut and the trunnion fork end due to the installation of the ball nut being offset 180 degrees after maintenance. Such interference between the ball nut and trunnion fork end could lead to fracture of the lead screw of the position 1 flap screw jack. This condition, if not corrected, could result in failure of the tie bar and possible disconnection of the flap structure from the airplane.

Explanation of Relevant Service Information

The manufacturer has issued Airbus Service Bulletin A310-27-2075, Revision 02, dated February 8, 2000, which describes procedures for modification of the position 1 flap screw jack. The modification involves the installation of a bracket, which will prevent incorrect installation of the ball nut. The DGAC classified this service bulletin as mandatory and issued French airworthiness directive 1999-510-299(B), dated December 29, 1999, in order to assure the continued airworthiness of these airplanes in France.

The Airbus service bulletin references Lucas/Liebherr Service Bulletin 537-27-M537-15, dated May 12, 1994, as an additional source of service information for accomplishing the modification proposed by this AD.

FAA's Conclusions

This airplane model is manufactured in France and is type certificated for operation in the United States under the provisions of section 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. Start Printed Page 20922

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 modification of the position 1 flap control screw jack. The actions would be required to be accomplished in accordance with the Airbus service bulletin described previously.

Cost Impact

The FAA estimates that 41 airplanes of U.S. registry would be affected by this proposed AD, that it would take approximately 2 work hours per airplane to accomplish the proposed modification, and that the average labor rate is $60 per work hour. Required parts would cost approximately $105 per airplane. Based on these figures, the cost impact of the proposed modification AD on U.S. operators is estimated to be $9,225, or $225 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.

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List of Subjects in 14 CFR Part 39

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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:

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PART 39—AIRWORTHINESS DIRECTIVES

1. The authority citation for part 39 continues to read as follows:

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Authority: 49 U.S.C. 106(g), 40113, 44701.

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[Amended]

2. Section 39.13 is amended by adding the following new airworthiness directive:

Airbus Industrie: Docket 2000-NM-77-AD.

Applicability: Model A310 series airplanes, certificated in any category, except those airplanes on which Airbus Modification 10855 or Airbus Service Bulletin A310-27-2075 has been accomplished.

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 fracture of the lead screw of the position 1 flap screw jack, which could result in failure of the tie bar and possible disconnection of the flap structure from the airplane, accomplish the following:

Modification

(a) Within 18 months after the effective date of this AD, modify the position 1 flap screw jack in accordance with Airbus Service Bulletin A310-27-2075, Revision 02, dated February 8, 2000.

Note 2:

Modifications accomplished prior to the effective date of this AD, in accordance with Airbus Service Bulletin A310-27-2075, dated November 18, 1994, or Revision 01, dated July 20, 1995, are considered acceptable for compliance with the modification specified by this AD.

Note 3:

The Airbus service bulletin references Lucas/Liebherr Service Bulletin 537-27-M537-15, dated May 12, 1994, as an additional source of service information for accomplishing the applicable action required by this AD.

Spares

(b) As of the effective date of this AD, no person shall install on any airplane a position 1 flap screw jack having part number 537G0000-02, unless modified in accordance with this AD.

Alternative Methods of Compliance

(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 4:

Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the International Branch, ANM-116.

Special Flight Permits

(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.

Note 5:

The subject of this AD is addressed in French airworthiness directive 1999-510-299(B), dated December 29, 1999.

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Issued in Renton, Washington, on April 13, 2000.

Charles D. Huber,

Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.

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[FR Doc. 00-9823 Filed 4-18-00; 8:45 am]

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